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Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Применить Всего найдено 17928. Отображено 200.
10-03-2011 дата публикации

ФЮЗЕЛЯЖ ЛЕТАТЕЛЬНОГО АППАРАТА

Номер: RU2413651C2

Изобретение относится к фюзеляжу летательного аппарата. Фюзеляж содержит пуленепробиваемый слой, а также элемент системы изоляции, который содержит заполнитель и оболочку. Заполнитель также содержит пуленепробиваемый слой. Пуленепробиваемые слои имеют сотовую структуру. Достигается улучшение пуленепробиваемых свойств фюзеляжа. 10 з.п. ф-лы, 11 ил.

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20-05-2004 дата публикации

СИСТЕМА ЗАЩИТЫ САМОЛЕТА ОТ ОШИБОЧНЫХ ИЛИ УМЫШЛЕННЫХ ДЕЙСТВИЙ, ПРИВОДЯЩИХ К КАТАСТРОФЕ

Номер: RU2228885C2

Система относится к области авиационного оборудования и предназначена для установки на гражданские летательные аппараты (ЛА) для защиты ЛА в критических – катастрофических ситуациях. Технический результат заключается в создании автоматизированной управляющей системы защиты самолета от ошибочных или умышленных действий экипажа, приводящих к катастрофе. Система содержит датчики состояния бортовых систем, соединенных с каналом информационного обмена, штатную и аварийную системы управления ЛА, бортовую линию радиоуправления воздушным движением, три экспертные системы (ЭС), вычислитель момента блокировки экипажа, систему блокировки действий экипажа, вычислитель параметров движения летательного аппарата, три переключателя. 1 ил.

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10-12-2004 дата публикации

УСТРОЙСТВО ДЛЯ ЗАЩИТЫ ОТ КОНТАКТОВ С ЛОПАСТЯМИ ВОЗДУШНОГО ВИНТА ЛЕТАТЕЛЬНОГО АППАРАТА

Номер: RU2241638C2

Изобретение относится к области авиации и может быть использовано на летательных аппаратах (ЛА), конструкция которых предполагает возможность соударения лопастей при выходе величины их махового движения за заданные пределы с элементами конструкции ЛА и/или с окружающими объектами, например с земной поверхностью. Устройство содержит защитный элемент с контактной поверхностью и средства его сопряжения с элементами конструкции летательного аппарата. При этом точки контактной поверхности защитного элемента лежат в пределах условного цилиндра, ось которого расположена в области расчетных положений оси вращения воздушного винта, а его поверхность описана вокруг области заданных положений лопастей воздушного винта, к которой обращена контактная поверхность защитного элемента, по меньшей мере, отдельные фрагменты которой выполнены гладкими в направлении окружного движения лопастей воздушного винта. Контактная поверхность защитного элемента может быть выполнена плоской или выпуклой в сторону области ...

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01-10-2018 дата публикации

СИСТЕМА ДИСТАНЦИОННОЙ СВЯЗИ ДЛЯ ЛЕТАТЕЛЬНОГО АППАРАТА

Номер: RU2668449C2

Изобретение относится к системе дистанционной связи, выполненной с возможностью встраивания в летательный аппарат (1А, 1B, 1С), содержащий по меньшей мере один винт (50А, 50B, 50С) двигателя с множеством лопастей (52А, 52B, 52С), выполненный с возможностью вращения относительно неподвижного модуля (10А, 10B, 10С) летательного аппарата вокруг оси (X) двигателя. Система дистанционной связи содержит: оптическое излучающее устройство, выполненное, когда система встроена в летательный аппарат (1А, 1B, 1С), с возможностью излучать световой пучок, который выходит снаружи винта (50А, 50B, 50С) из по меньшей мере одной излучающей поверхности (54А, 54B, 54С) указанного винта (50А, 50B, 50С); и оптическое устройство обнаружения светового пучка, содержащее по меньшей мере одну обнаруживающую поверхность (14А, 14B, 14С), являющуюся чувствительной к световому пучку, и встроенное в неподвижный модуль (10А, 10B, 10С) таким образом, чтобы указанная по меньшей мере одна излучающая поверхность (54А, 54B, ...

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11-10-2017 дата публикации

ПАРАМЕТРИЗУЕМАЯ СИСТЕМА ДЛЯ ЦЕНТРАЛИЗОВАННОГО ТЕХНИЧЕСКОГО ОБСЛУЖИВАНИЯ, ПРЕДНАЗНАЧЕННАЯ ДЛЯ ЛЕТАТЕЛЬНОГО АППАРАТА

Номер: RU2633015C2
Принадлежит: ТАЛЬ (FR)

Группа изобретений относится к системе и способу централизованного обслуживания летательного аппарата (ЛА) и способу разработки такой системы. Система содержит устройства, способные выдавать сообщения о неисправностях или аварийные сообщения, ядро программного обеспечения, параметризируемое с помощью базы данных двоичных параметров (БД), содержащее не меньше четырех элементарных ячеек, каждая из которых содержит параметризируемый БД программный движок. Для осуществления способа централизованного обслуживания производят сбор сообщений о неисправностях и аварийных сообщений, их диагностирование и отображение отчета на графическом интерфейсе, устанавливают связь между оператором технического обслуживания и совокупностью устройств ЛА. Для разработки системы с помощью параметризации определяют область конфигурации для эксплуатационных требований системы для централизованного технического обслуживания, программируют и сертифицируют несколько общих программных движков. Обеспечивается централизованное ...

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20-05-2010 дата публикации

ДВЕРЬ, ПРЕДНАЗНАЧЕННАЯ ДЛЯ ЗАКРЫТИЯ ПРОХОДА ВНУТРИ ВОЗДУШНОГО СУДНА

Номер: RU2389658C2

Изобретение относится к двери воздушного судна, предназначенной для перекрытия прохода внутри воздушного судна. Дверь содержит по меньшей мере одно окошко, позволяющее обеспечить прохождение воздуха, а также по меньшей мере одну эластичную мембрану, перекрывающую это окошко. Эластичная мембрана содержит с одной стороны зону, непроницаемую для воздуха, располагающуюся против окошка и перекрывающую его полностью, а с другой стороны - зону, проницаемую для воздуха и располагающуюся в непосредственной близости от упомянутой непроницаемой зоны. Изобретение повышает безопасность кабины экипажа. 2 н. и 8 з.п. ф-лы, 14 ил.

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20-02-2009 дата публикации

СИСТЕМА ЩИТКОВ НА КРЫЛЕ САМОЛЕТА С ЖЕСТКИМ КРЫЛОМ

Номер: RU2346851C2

Изобретение относится к летательным аппаратам, в частности к системе щитков на крыле летательного аппарата. Система щитков состоит из средств содействия подъемной силе в виде предкрылков и/или закрылков, подвижным образом размещенных на передней кромке и/или задней кромке крыла. Система щитков содержит блок управления щитками для регулировки изменения положения щитков на крыле, несколько групп щитков, каждая из которых содержит средство содействия подъемной силе, и несколько приводных станций, каждая из которых относится к одной группе щитков. Приводная станция включает в себя два привода, проводящим образом связанных с блоком управления щитков, и два дополнительных устройства механической связи приводов со средствами содействия подъемной силе. Группы щитков управляются индивидуально посредством соответствующих этим группам щитков приводных станций. Решение направлено на повышение функциональности щитков одновременно с повышением гибкости функционирования системы щитков. 17 з.п. ф-лы, 7 ...

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27-07-2015 дата публикации

СПОСОБ КОНТРОЛЯ ПАРАМЕТРОВ ПОЛЕТА НАЗЕМНЫМ РЕГИСТРАТОРОМ

Номер: RU2558167C2

Изобретение относится к способам контроля и регистрации параметров полета самолета или вертолета. Способ контроля параметров полета наземным регистратором заключается в передаче видеоизображения приборной доски самолета на командный пункт управления, причем передачу видеосигнала осуществляют на заранее выделенных и зарегистрированных радиочастотах. При этом в кабине пилотов на бортовом держателе жестко устанавливают смартфон таким образом, чтобы его объектив обеспечивал на экране смартфона изображение приборной доски, положение командно-контрольных органов самолета, а также положение и действие пилотов. Для регистрации речевой информации экипажа используют микрофон смартфона. Одновременно видео и звуковой сигналы со смартфона передают с помощью спутниковой, сотовой мобильной связи на наземный регистратор, где осуществляют видео и аудиозапись параметров полета от взлета до посадки самолета, затем видео и аудиозаписи наземного регистратора используют для технического анализа результатов полета ...

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19-04-2018 дата публикации

СИСТЕМА ОБНАРУЖЕНИЯ ЛАЗЕРНОГО ВОЗДЕЙСТВИЯ И ОПОВЕЩЕНИЯ О НЕМ

Номер: RU2651306C2
Принадлежит: Зе Боинг Компани (US)

Изобретение относится к области обнаружения электромагнитных излучений, в частности лазерного. Система обнаружения лазерного воздействия и оповещения о нем пилота воздушного летательного аппарата содержит обнаруживающее устройство, выполненное с возможностью установки на воздушный летательный аппарат, имеющее оптическую подсистему, обнаруживающую подсистему и обрабатывающую подсистему для определения характеристик поступающего лазерного излучения и передачи оповещающего о лазере выходного сигнала. Выходной сигнал содержит спектральные характеристики лазерного излучения, тип соответствующих средств защиты глаз и местоположение источника лазерного излучения. Устройство обработки цифрового сигнала выполнено с возможностью определения азимута и угла места источника лазерного излучения. Способ обнаружения лазерного излучения включает обнаружение излучения, создание цифрового сигнала и обработку полученного сигнала. Обеспечивается надежное обнаружение и идентификация лазерного излучения. 2 н.

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07-09-2018 дата публикации

ДАТЧИК ПОДЪЕМНОЙ СИЛЫ ЛЕТАТЕЛЬНОГО АППАРАТА

Номер: RU2666497C2

Группа изобретений относится к датчикам подъемной силы летательного аппарата и способу определения доступной подъемной силы. Датчик подъемной силы в одном варианте содержит флюгерный датчик на передней кромке крыла, привод, связанный с флюгерным датчиком, LC-цепь, расположенные определенным образом, процессор. Датчик подъемной силы во втором варианте содержит флюгерный датчик, компрессор, связанный с флюгерным датчиком, LC-цепь, процессор. LC-цепь содержит индукционную катушку и осциллятор. Для определения доступной подъемной силы измеряют изменение частоты колебаний LC-цепи, вызванное изменением положения привода, связанного с флюгерным датчиком. Обеспечивается повышение надежности и чувствительности датчика подъемной силы. 3 н. и 16 з.п. ф-лы, 11 ил.

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11-10-2021 дата публикации

Исполнительный орган для приведения в действие приспособления летательного аппарата

Номер: RU2757103C2

Группа изобретений относится к исполнительному органу для приведения в действие приспособления управления полетом летательного аппарата и летательному аппарату, который его содержит. Исполнительный орган содержит два бесконтактно работающих датчика, один из которых расположен в пути нагрузки исполнительного органа, а другой - вне пути нагрузки. Обеспечивается уменьшение чувствительности к помехам. 2 н. и 11 з.п. ф-лы, 12 ил.

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20-11-2009 дата публикации

УСТРОЙСТВО ДЛЯ ПРЕДОТВРАЩЕНИЯ ВЫКАТЫВАНИЯ ВОЗДУШНЫХ СУДОВ ЗА ПРЕДЕЛЫ ВЗЛЕТНО-ПОСАДОЧНОЙ ПОЛОСЫ

Номер: RU2373115C1

Изобретение относится к авиационной технике для проектирования оборудования бортовой навигации и системы управления реверсом обратной тяги двигателей, для предотвращения выкатывания или снижения степени разрушения воздушного судна в условиях посадки на скользкую взлетно-посадочную полосу. Устройство содержит систему определения местоположения (1), базу данных (3), содержащую информацию относительно взлетно-посадочной полосы, и ЭВМ (4), а так же систему сигнализации (9) и подачи сигнала в автомат управления тягой, если потребная для остановки дистанция превышает фактическое расстояние до торца полосы. Блок связи с бортовым оборудованием (1) содержит блок управления механизмом блокировки рычага управления реверсом тяги (7) и блок связи с автоматом управления тягой (8). В ЭВМ введены блок вычисления текущего отрицательного ускорения для текущих значений скорости и ускорения (5), соединенный с блоком расчета фактической дистанции до торца взлетно-посадочной полосы (6). Достигается повышение ...

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27-07-2013 дата публикации

БОРТОВОЙ КОМПЛЕКС ИНДИВИДУАЛЬНОЙ ЗАЩИТЫ ЛЕТАТЕЛЬНОГО АППАРАТА ОТ УПРАВЛЯЕМЫХ РАКЕТ С ИНФРАКРАСНЫМИ ГОЛОВКАМИ САМОНАВЕДЕНИЯ

Номер: RU130586U1

Бортовой комплекс индивидуальной защиты летательного аппарата от управляемых ракет с инфракрасной головкой самонаведения, содержащий устройство формирования излучения активной помехи, сопряженное через линию передачи команд управления с устройством формирования управляющего воздействия, задающий орган которого выполнен в виде системы дистанционной регистрации ультрафиолетовой составляющей излучения факела реактивного двигателя атакующей управляемой ракеты, отличающийся тем, что воспринимающий элемент системы дистанционной регистрации ультрафиолетовой составляющей излучения факела реактивного двигателя атакующей управляемой ракеты выполнен с возможностью регистрации излучения в солнечно-слепом диапазоне ультрафиолетового излучения короче 280 нм.

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10-09-2010 дата публикации

ИНТЕГРИРОВАННЫЙ АВИАЦИОННЫЙ МНОГОФУНКЦИОНЫЙ ИНДИКАТОР

Номер: RU97339U1

Интегрированный авиационный многофункциональный индикатор, содержащий жидкокристаллический экран, блок датчиков параметров ЖКЭ и органов управления, блок исполнительных устройств, блок управления режимами работы, а также взаимосоединенные входами-выходами по магистрали информационного обмена вычислительные модули базы исходных данных и адаптер ввода-вывода и управления информационным обменом, причем блок управления режимами работы соединен с адаптером ввода-вывода-управления информационным обменом, подключенными входами-выходами к магистрали командно-информационного обмена адаптером информации о рельефе земной поверхности, адаптером телевизионной информации, адаптером радиолокационной метеоинформации, графическим процессором, соединенным с устройством сглаживания изображений, отличающийся тем, что графический процессор соединен с блоком датчиков параметров ЖКЭ и органов управления, жидкокристаллическим экраном, блоком исполнительных устройств, а магистралью видеоинформации фонового изображения ...

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20-12-2012 дата публикации

СТАРТОВАЯ СИСТЕМА ПРЕДУПРЕЖДЕНИЯ КРИТИЧЕСКИХ РЕЖИМОВ ОДНОВИНТОВОГО ВЕРТОЛЕТА

Номер: RU122983U1

Стартовая система предупреждения критических режимов одновинтового вертолета, содержащая канал измерения, канал формирования эксплуатационных ограничений, канал индикации, канал сигнализации, отличающаяся тем, что канал измерения включает аэрометрический канал определения величины, направления и составляющих вектора скорости ветра, спутниковый канал позиционирования и канал определения пространственного углового положения вертолета, при этом канал формирования эксплуатационных ограничений включает каналы определения допустимых значений углов крена и тангажа, скорости и направления ветра, продольной и боковой составляющих вектора скорости ветра на стоянке, на стартовых и взлетно-посадочных режимах, а каналы индикации и сигнализации включают соответственно каналы отображения текущих и допустимых значений критических параметров эксплуатационных ограничений на стартовых и взлетно-посадочных режимах.

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Номер: RU156448U1

... 1. Бортовой регистратор, содержащий:корпус, имеющий проходящую внутрь выемку, образованную в его наружной периферической поверхности;электронный интерфейс, расположенный внутри корпуса, электронный интерфейс присоединен для приема данных;блок памяти, расположенный внутри корпуса и электрически присоединенный к электронному интерфейсу для сохранения данных; ирезервный источник питания, физически и съемным образом расположенный в пределах выемки и внешний относительно корпуса, резервный источник питания имеет электрический разъем, присоединенный к ответному электрическому разъему корпуса для обеспечения рабочего напряжения на электронный интерфейс и блок памяти, при этом физические размеры резервного источника питания и электрического разъема помещаются в пределах конструктива, который является предопределенным для корпуса применяемым стандартом.2. Бортовой регистратор по п. 1, дополнительно включающий в себя фиксатор для крепления резервного источника питания к корпусу.3. Бортовой регистратор ...

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Номер: RU2370416C1

Изобретение относится к области авиационного бортового оборудования и предназначено для установки на гражданские летательные аппараты (ЛА). Система включает бортовую линию радиоуправления, соединенную с наземной линией радиоуправления пункта управления воздушным движением, штатную систему управления ЛА (18), систему автоматического управления (САУ) (17), соединенные с датчиками состояния бортовых систем, первую экспертную систему (ЭС) (2) с вычислительным блоком определения режима полета (3), соединенным с базой знаний (БЗ) по признакам режима полета (4), вторую ЭС (5) с блоком определения катастрофической ситуации (КС) (6), соединенным с БЗ по КС (7), вычислитель параметров движения (ВПД) ЛА (1), третью ЭС (14) с вычислительным блоком управления по выводу из КС (15) и базу данных по виду управления вывода из КС (16), вычислительный блок момента блокировки экипажа (12), четвертую ЭС с вычислительным блоком по определению времени невмешательства (БОВН) летчика в управление ЛА при КС за время ...

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Номер: RU2215669C1

Изобретение относится к технике защиты летательных аппаратов от поражения. В потоке газа устанавливают экранирующее приспособление, выполненное в виде противорадиолокационной и противоинфракрасной решеток, уменьшающих акустическую заметность. Противоинфракрасную решетку располагают ближе к двигателю силовой установки, чем противорадиолокационную решетку, а последнюю располагают за противоинфракрасной решеткой в направлении против полета летательного аппарата. Изобретение обеспечивает повышенную защиту летательного аппарата благодаря уменьшению заметности силовой установки во всех ракурсах ее экранирования. 16 з.п.ф-лы, 1 табл., 17 ил.

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Устройство для обезвреживания террористов в гражданских самолетах предназначено для повышения безопасности полетов, в частности, для пресечения действий по захвату самолетов. Устройство содержит салон с рядами пассажирских кресел /1/, образующих проход /2/ к кабине пилотов, снабженный расположенной в верхней части салона видеокамерой общего обзора. Пол /3/ в зоне прохода /2/ покрыт съемным покрытием, выполненным в виде отдельных прямоугольных поперечных участков /4/, при этом один из обращенных к креслу краев каждого участка /4/ соединен с ремнем /5/, проходящим через отверстие /6/ в боковине кресла вблизи пола и намотанным на барабан /7/ на валу /8/ установленного под соответствующим креслом микродвигателя /9/, a противоположный край участка /4/ прикреплен к полу /3/ с помощью липучек /10/. На полу /3/ под участками /4/ покрытия размещены фиксирующие человека элементы /11/, a обмотки возбуждения микродвигателей /9/ соединены с источником электрического сигнала с помощью кнопок на пульте ...

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Номер: RU190804U1

Полезная модель относится к радиотехнике и предназначена для обеспечения управления полетом корабельных летательных аппаратов (ЛА), оснащенных соответствующим оборудованием на всех этапах полета ЛА, полетом по маршруту, вывода летательного аппарата в зону действия посадочных средств корабля, обеспечения посадки корабельного летательного аппарата по сигналам управления, передаваемыми по радиоканалу, формируемыми посадочными средствами корабля. Технический результат состоит в повышении целостности управления полетом ЛА. Для достижения технического результата устройство для обеспечения навигации и посадки корабельных летательных аппаратов состоит из блоков: азимутально-дальномерного радиомаяка с антенной, аппаратуры передачи данных, посадочного следящего радиолокатора, процессора вторичной обработки посадочного следящего радиолокатора, при этом выход канала опознавания азимутально-дальномерного радиомаяка соединен со входом процессора вторичной обработки посадочного следящего радиолокатора ...

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Номер: RU2318701C1

Изобретение относится к средствам для повышения безопасности полетов гражданских самолетов, в частности для пресечения действий по захвату самолета. Устройство для предотвращения захвата гражданского самолета размещено на креслах, установленных в салоне самолета. Каждое из кресел содержит каркас, сиденье, спинку и боковины с подлокотниками, в обеих боковинах каждого кресла над бедрами пассажира выполнены полости. В одной полости размещен резервуар, соединенный с концом упругого эластичного рукава и заполненный вместе с рукавом порошком с ферромагнитными свойствами, причем другой конец рукава закрыт и установлен с возможностью свободного входа внутрь кресла через отверстие в боковине, снабженное магнитным фиксатором. В другой полости напротив места выхода рукава размещен электромагнит, обмотка которого подключена к соответствующим данному креслу контактам специального пульта в кабине пилотов с указанием номера кресла, соединенным с источником изменяемого электрического сигнала. Данное техническое ...

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Номер: RU2252899C1

Изобретение предназначено для построения высокоманевренных многоцелевых самолетов, действующих в составе группы. Самолет содержит фюзеляж, крыло, оперение, шасси, основную и вспомогательную силовые установки, воздухозаборники и многопозиционный интегрированный комплекс бортового оборудования. Комплекс включает в себя систему информационного обмена, бортовую цифровую вычислительную систему управления полетом и учебно-боевыми действиями, внешнее запоминающее устройство и систему ввода информации, инерциальную и радиотехническую системы навигации и посадки, ответчик системы управления воздушным движением и госопознавания, радиокомпас, радиовысотомер, маркерный приемник, комплексную систему управления самолетом, систему управления вооружением, комплексную системы электронной индикации, управления и прицеливания, информационные табло аварийной сигнализации, систему спутниковой связи, систему управления общесамолетным оборудованием, бортовую систему объективного контроля, связную радиостанцию ...

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Номер: RU2598130C1

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Номер: RU2578756C1

Изобретение относится к вычислительной технике. Технический результат - повышение быстродействия системы. Система содержит: модуль идентификации базового адреса данных эксплуатации воздушных судов авиакомпании; модуль идентификации относительного адреса данных эксплуатации воздушных судов одного типа; модуль селекции адреса параметров класса особых ситуаций (ОС); модуль вызова подпрограммы вычисления обратного значения суммарного налета; модуль регистрации параметров класса ОС; модуль селекции класса ОС без инцидентов; модуль селекции базового адреса параметров подклассов класса ОС; модуль распознавания ветви процедуры вычисления вероятностей возникновения ОС; модуль принятия решения об уровне безопасности полетов по суммарным вероятностям классов ОС; модуль принятия решения об уровне безопасности полетов по сигнальным вероятностям классов ОС; модуль идентификации сигнальных вероятностей подклассов класса ОС; модуль принятия решения об уровне безопасности полетов по сигнальным вероятностям ...

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Номер: RU2789042C1

Изобретение относится к области вычислительной техники. Технический результат заключается в повышении эффективности выполнения дальнего воздушного боя пар истребителей. Технический результат достигается за счет системы интеллектуальной поддержки летчиков-истребителей в дальнем воздушном бою с парой истребителей противника, которая содержит блок обработки входящей информации, блок конфигурации (2×2) ДБВ M×N, осуществляющий выдачу рекомендации по тактическому приему и целям на атаку; блок конфигурации (2×1) ДБВ M×N, осуществляющий выдачу рекомендации по тактическому приему и цели на атаку; блок конфигурации (1×2) ДБВ M×N, осуществляющий выдачу рекомендации по тактическому приему и цели на атаку; блок, определяющий условия начала ДБВ 1×1; блок, формирующий рекомендации по проблемным субституциям ДБВ 1×1; блок подготовки информации для информационно-управляющего поля (ИУП). 1 ил.

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Номер: RU2297596C1

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Использование для предотвращения захвата и угона летательного аппарата террористами. Сущность изобретения: на террористов воздействуют газообразным химическим веществом, безвредным для здоровья, а также лазерным или высокочастотным излучением.

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Номер: RU2740440C1

Изобретение относится к сельскому хозяйству и к области защиты аэропортов от пернатых. Способ отпугивания пернатых в процессе взлета самолета заключается в том, что формируют коридор из непрерывно мигающих световых лучей и беспрерывных вспышек сигнальных ракет. При этом упомянутый коридор формируют непосредственно перед взлетающим самолетом по его курсу из расходящихся лучей света (9) от трех прожекторов (6), закрепленных на фюзеляже (1). Коридор действует на протяжении всего прохождения самолетом опасной из-за пернатых зоны. Достигается повышение безопасности взлета самолета. 8 ил.

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27-06-2007 дата публикации

СПОСОБ И СИСТЕМА ПРЕДОТВРАЩЕНИЯ ЗАХВАТА САМОЛЕТА

Номер: RU2302039C1

Изобретение относится к области средств безопасности авиационных пассажирских и грузопассажирских самолетов. Технический результат заключается в более точном наведении оружия на террористов. Захват стоящего на земле самолета предотвращают путем обнаружения террориста и его уничтожения при помощи стрелкового оружия. Наведение стрелкового оружия на террориста осуществляют посредством вычисления координат расположения террориста и дистанционно-управляемого стрелкового оружия и расчета установки стрелкового оружия. Обнаружение террориста осуществляют при помощи, по крайней мере, одной управляемой видеокамеры, установленной в салоне самолета и подключенной через бортовой компьютер к передатчику самолета. Уничтожение террориста осуществляют путем стрельбы по нему из дистанционно-управляемого стрелкового оружия через обшивку самолета с применением управляющего компьютера. 2 н. и 3 з.п. ф-лы, 6 ил.

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10-06-2008 дата публикации

УСТРОЙСТВО ДЛЯ ОБЕЗВРЕЖИВАНИЯ ТЕРРОРИСТОВ В ГРАЖДАНСКИХ САМОЛЕТАХ

Номер: RU2326024C1

Изобретение относится к защитному оборудованию гражданских самолетов и предназначено для пресечения действий по захвату самолетов. Устройство содержит расположенную в проходе салона между рядами кресел под полом фюзеляжа полость с дном. Пол в зоне прохода выполнен в виде упругосоединенных пар пластин, установленных в направляющих с возможностью сдвижения-раздвижения с помощью пружин. Имеющиеся на дне выступы обеспечивают заданную жесткость пола. Пластины соединены перекинутыми через блоки тросами с сердечниками электромагнита, установленного на дне полости. На пластинах наклеены тензорезисторы, включенные в мостовую измерительную цепь. На торцах пластин установлены контактные проводники. Обмотки возбуждения и контактные проводники соединены с источниками импульсного и плавноизменяемого электрических сигналов. Первый из источников обеспечивает раздвижение пластин с захватом ног террориста, а второй - пропускание через тело террориста электрического тока заданной амплитуды. Изобретение повышает ...

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06-12-2021 дата публикации

СПОСОБ ОПРЕДЕЛЕНИЯ ОСТАТОЧНОГО РЕСУРСА ТОРМОЗНЫХ УСТРОЙСТВ ЛЕТАТЕЛЬНЫХ АППАРАТОВ

Номер: RU2761124C1

Изобретение относится к способу определения остаточного ресурса тормозных устройств летательных аппаратов (ЛА). Для определения остаточного ресурса во время посадки ЛА фиксируют моменты времени и скорости прохождения его центра масс в зоне получения данных, которая расположена по всей площади посадочной полосы, производят расчет дистанции торможения, затем формируют массив данных о дистанциях торможения и неоднородностях замедления по дистанции торможения, моментах времени и количестве произведенных посадок летательного аппарата, производят расчет суммарной дистанции торможения за текущий срок эксплуатации ЛА с учетом неоднородностей замедления по дистанциям торможения и рассчитывают количество оставшихся посадок безаварийной работы тормозных устройств, сравнивают полученное значение с заявленным количеством посадок безаварийной работы и принимают решение о дальнейшей эксплуатации тормозных устройств летательного аппарата. Обеспечивается повышение точности определения остаточного ресурса ...

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10-09-2008 дата публикации

ДВЕРЬ, ПРЕДНАЗНАЧЕННАЯ ДЛЯ ЗАКРЫТИЯ ПРОХОДА ВНУТРИ ВОЗДУШНОГО СУДНА

Номер: RU2007107920A
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... 1. Дверь (12), предназначенная для закрытия прохода внутри воздушного судна, отличающаяся тем, что она содержит устройство, позволяющее обеспечить прохождение потока воздуха через эту дверь в одном направлении, но препятствующее прохождению воздуха в противоположном направлении. 2. Дверь (12) по п.1, отличающаяся тем, что она содержит по меньшей мере одно окошко (74), позволяющее обеспечить прохождение воздуха, а также по меньшей мере одну эластичную мембрану (76), причем эта эластичная мембрана (76) может быть деформирована в диапазоне между некоторым первым положением, в котором она перекрывает все упомянутое окошко (74), и некоторым вторым положением, в котором преобладающая часть этой эластичной мембраны (76) удалена от этого окошка (74). 3. Дверь (12) по п.2, отличающаяся тем, что крышка (78) располагается на некотором расстоянии от окошка (74) со стороны мембраны (76) с возможностью ограничения деформации этой мембраны (76). 4. Дверь (12) по п.3, отличающаяся тем, что упомянутая крышка ...

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20-10-2005 дата публикации

ПУЛЬТ ВЫБОРА СИСТЕМ

Номер: RU2004107896A
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Пульт выбора систем, предназначенный для указания системе индикации летательного аппарата от какой из систем-датчиков брать параметры на индикацию, и включающий микроконтроллер, кнопки, индикатор, фотодатчики, энергонезависимое запоминающее устройство, интерфейсную часть и блок питания, а микроконтроллер в своем составе содержит долговременное запоминающее устройство, оперативное запоминающее устройство и аналого-цифровой преобразователь, к микроконтроллеру подключены кнопки, индикатор, энергонезависимое запоминающее устройство и интерфейсная часть, к аналого-цифровому преобразователю микроконтроллера подключены фотодатчики.

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10-04-2005 дата публикации

ЭЛЕКТРОРАСПРЕДЕЛИТЕЛЬНОЕ УСТРОЙСТВО ПЕРЕМЕННОГО ТОКА ЛЕТАТЕЛЬНОГО АППАРАТА

Номер: RU2003130415A
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Электрораспределительное устройство переменного тока летательного аппарата, содержащее защитную аппаратуру сети, установленную на основании на функциональных шинах устройства, и клеммы подключения питания от источников электроэнергии с распределительными шинами, отличающееся тем, что однофазные аппараты защиты размещены на основании в рядах в шахматном порядке, а питание функциональных шин как однофазным, так и трехфазным токами выполнено с двух сторон от разных контактных точек, при этом функциональные шины однофазных аппаратов защиты выполнены гребенчатого вида, лепестки которых присоединены к контактам указанных аппаратов защиты, а функциональные шины трехфазных аппаратов защиты выполнены изолированным проводом, в разрывах изоляции которого укреплены кабельные наконечники, присоединенные к контактам аппаратов защиты соответствующих фаз.

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10-08-2002 дата публикации

СПОСОБ УПРАВЛЕНИЯ РЕЖИМАМИ СВЯЗИ САМОЛЕТА

Номер: RU2000124082A
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... 1. Способ управления режимами связи для обмена в цифровом виде сообщениями между землей и самолетом, оснащенным аппаратурой связи, которая пригодна для связи через авиационные системы цифровой связи ACARS (авиационная бортовая система адресования и передачи сообщений) и ATN (система авиационной связи) и для связи через их различные подсети (10-13, 20 и 21) передачи, а также оснащенным процессором (30), который служит для управления связью самолета в системе ACARS или ATN, и интерфейсом (31) человек-машина, который служит для взаимодействия пилота с указанным процессором (30), отличающийся тем, что для вышеуказанного процессора (30) создают базу (342) данных, в которой в каждый момент времени содержатся информация об обновленном состоянии режимов связи через подсеть обеих систем ACARS или ATN, зарегистрированных в качестве доступных для самолета в необходимый момент обмена информацией, с учетом функциональных возможностей как наземного оборудования связи в зоне, над которой пролетает самолет ...

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20-02-2010 дата публикации

СПОСОБ И СИСТЕМА ЛИКВИДАЦИИ В ПОЛЕТЕ ТЕРРОРИСТОВ, ЗАХВАТИВШИХ ПАССАЖИРСКИЙ САМОЛЕТ

Номер: RU2008117668A
Принадлежит:

... 1. Способ ликвидации в полете террористов, захвативших пассажирский самолет при помощи, по меньшей мере, одной единицы дистанционно-управляемого стрелкового оружия, наведение которого на цель осуществляют, используя изображение с видеокамер, расположенных в салоне пассажирского самолета, выведенное на экран монитора, отличающийся тем, что наведение на террориста единицы дистанционно-управляемого стрелкового оружия, установленного на боевом самолете, осуществляют посредством приводов, разворачивающих стрелковое оружие на углы, полученные в результате расчета координат террориста относительно радиомаяков пассажирского самолета, и радиолокатора, установленного на боевом самолете, а прицеливание дистанционно-управляемого стрелкового оружия на террориста осуществляют с учетом расстояния от радиолокатора до каждой единицы дистанционно-управляемого стрелкового оружия боевого самолета. ! 2. Способ ликвидации в полете террористов, захвативших пассажирский самолет, по п.1, отличающийся тем, что координаты ...

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20-12-2007 дата публикации

СПОСОБ ОГРАНИЧЕНИЯ НАГРУЗКИ В ПРИВОДНЫХ СИСТЕМАХ ДЛЯ СИСТЕМЫ С БОЛЬШОЙ ПОДЪЕМНОЙ СИЛОЙ ДЛЯ САМОЛЕТОВ

Номер: RU2006115480A
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... 1. Способ ограничения силовой нагрузки в системе для увеличения подъемной силы летательных аппаратов, имеющей разветвленную приводную систему для механической передачи мощности к приводным агрегатам (25) отдельных секций (3, 4, 5, 6; 103, 104, 105, 106) систем посадочных закрылков и/или систем отклоняемых предкрылков, посредством соответствующих кинематических цепей (8, 9; 108, 109), датчики (15, 16, 17; 115, 116, 117) положений и приводной агрегат (7; 107), при котором сигналы измеряются (231), по меньшей мере, с помощью двух датчиков положений, отличающийся тем, что он предусматривает расчет (232), по меньшей мере, одной опорной переменной величины по измеренным сигналам; сравнение (233) каждой опорной переменной величины с соответствующей пороговой величиной, которую предварительно определяют по максимально допустимой силовой нагрузке; и выработку (236) сигнала управления для того, чтобы управляемым способом ограничивать подачу мощности к приводному агрегату (7; 107) в пределах ограничения ...

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17-03-2020 дата публикации

ЛАЗЕРНЫЙ ОСВЕТИТЕЛЬ ДЛЯ КОЛЛИМАТОРНОГО АВИАЦИОННОГО ИНДИКАТОРА

Номер: RU2716845C1

Изобретение относится к области оптического приборостроения и касается осветителя жидкокристаллического дисплея коллиматорного авиационного индикатора. Осветитель содержит несколько лазерных полупроводниковых излучателей, излучающих в зеленой области спектра, коллимирующие линзы, оптические клинья, направляющие излучение на гомогенизатор, и конденсор. Гомогенизатор состоит из двух наборов цилиндрических линз, расположенных взаимно перпендикулярно относительно друг друга, и находится в фокусе конденсора. Технический результат заключается в повышении максимальной яркости индицируемого изображения и обеспечении возможности его комфортного восприятия во всем диапазоне яркости окружающего пространства. 1 з.п. ф-лы, 2 ил.

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АВТОМАТИЗИРОВАННАЯ ЭКСПЕРТНАЯ СИСТЕМА КОЛИЧЕСТВЕННОЙ ОЦЕНКИ РИСКОВ БЕЗОПАСНОСТИ ПОЛЕТОВ ВОЗДУШНЫХ СУДОВ АВИАКОМПАНИИ

Номер: RU2716324C1

Изобретение относится к вычислительной технике, в частности к автоматизированной экспертной системе количественной оценки рисков безопасности полетов воздушных судов авиакомпании. Технический результат заключается в обеспечении возможности инициализации количественной оценки рисков безопасности полетов воздушных судов по экспертным оценкам как ущерба, так и эффективности барьеров по каждому из произошедших событий. Такой результат достигается за счет того, что система содержит модуль идентификации базового адреса количественной оценки рисков безопасности полетов воздушных судов авиакомпании, модуль идентификации относительного адреса количественной оценки рисков безопасности полетов воздушных судов одного типа, модуль идентификации базового адреса элементов матрицы-столбца экспертных оценок ущерба и эффективности барьеров события, модуль генерации сигналов считывания элементов матрицы-столбца экспертных оценок ущерба и эффективности барьеров события, модуль идентификации количественной ...

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10-04-2015 дата публикации

СПОСОБ ПОИСКА ПРИЗЕМЛИВШЕГОСЯ БЕСПИЛОТНОГО ЛЕТАТЕЛЬНОГО АППАРАТА

Номер: RU2546393C1

Изобретение относится к способу поиска приземлившегося беспилотного летательного аппарата (БЛА). При контакте БЛА с земной поверхностью автоматически активируется установленный на его борту маячковый передатчик, путем радиопеленгации которого определяют местоположение приземлившегося БЛА и осуществляют его розыск для последующей эвакуации. На борту БЛА дополнительно установлен блок светозвукового информирования, автоматически активирующийся в момент касания БЛА поверхности земли и выключающийся автоматически при подъеме БЛА на определенную высоту над поверхностью земли или вручную. Достигается сокращение времени поиска приземлившегося БЛА. 9 з.п. ф-лы.

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20-11-2006 дата публикации

АВИАЦИОННЫЙ МНОГОФУНКЦИОНАЛЬНЫЙ ИНДИКАТОР

Номер: RU2287459C1

Изобретение относится к области авиационного приборостроения, в частности к внутрикабинным приборам электронной индикации отображения параметров состояния летательного аппарата, бортового оборудования, радиолокационной обстановки. Индикатор содержит жидкокристаллический экран и блок управления режимами работы. В его состав также входят взаимосоединенные входами-выходами по магистрали информационного обмена вычислительные модули базы исходных данных и ввода-вывода-управления информационным обменом. Блок управления режимами работы соединен с устройством ввода-вывода-управления информационным обменом. Индикатор дополнительно снабжен устройством сглаживания изображений, а также подключенными входами-выходами к магистрали информационного обмена адаптером информации о рельефе земной поверхности, адаптером телевизионной информации, адаптером радиолокационной метеоинформации и устройством совмещения и наложения изображений. Последнее своими входами-выходами дополнительно соединено с жидкокристаллическим ...

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07-06-2018 дата публикации

Интегрированная система резервных приборов

Номер: RU2656954C1

Интегрированная система резервных приборов выполнена в виде отдельного блока, содержит датчики полного и статического давления, устройство обработки и преобразования сигналов, вычислитель, модуль пространственной ориентации, устройство управления режимами работы, магнитный зонд, жидкокристаллический индикатор, креноскоп, фотодатчик, устройство компенсации систематической составляющей смещения нуля инерциальных датчиков модуля пространственной ориентации, устройство списания девиационной погрешности с памятью, встроенную систему контроля, устройство анализа, устройство формирования изображения графика девиационных поправок, соединенных определенным образом. Обеспечивается повышение надежности и точности определения магнитного курса системы. 1 ил.

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27-03-2013 дата публикации

УСТРОЙСТВО ЗАЩИТЫ ДВИГАТЕЛЯ ОТ ПОПАДАНИЯ ПОСТОРОННИХ ПРЕДМЕТОВ

Номер: RU2011138828A
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Устройство защиты двигателя от попадания посторонних предметов, содержащее подвижную нижнюю панель, которая шарнирно соединена со штоком привода, жестко закрепленного на корпусе воздухозаборника, отличающееся тем, что нижняя панель выполнена с относительной длиной нижней панели, с относительной шириной нижней панелии способна к перемещению на относительную длину выдвижения нижней панели, равную от 0,6 до 0,3, при пропорциональном изменении относительной высоты расположения нижней кромки воздухозаборника от поверхности аэродромаот 0,8 до 1,25, установлена под углом α=15°-20° относительно оси передней кромки воздухозаборника и способна к совершению колебательных движений с периодом колебаний Т=1,0-4,0 с, где λ - длина выдвижения нижней панели, м; l - длина нижней панели, м; b - ширина нижней панели, м; Н - высота расположения нижней кромки воздухозаборника от поверхности аэродрома, м;- эквивалентный диаметр входа в воздухозаборник, м; А - высота воздухозаборника, м; В - ширина воздухозаборника ...

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27-10-2014 дата публикации

СПОСОБ ИДЕНТИФИКАЦИИ ВОЗДУШНОГО СУДНА ПРИ ПАРКОВКЕ У ВЫХОДА ДЛЯ ПАССАЖИРОВ ИЛИ НА МЕСТЕ СТОЯНКИ

Номер: RU2013119161A
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... 1. Способ идентификации воздушного судна при парковке у выхода для пассажиров или на месте стоянки для возможного присоединения пассажирского трапа (1) или загрузочного трапа к двери воздушного судна, причем воздушное судно располагают и останавливают в заданном местоположении с использованием бесконтактного измерения расстояния между воздушным судном и фиксированной точкой, и отображают расстояние на табло (6), установленном перед пилотом воздушного судна, например, на здании (7) аэровокзала, при этом показывают пилоту посредством табло (6) местоположение воздушного судна (5) относительно точки остановки для воздушного судна, а также тип паркующегося воздушного судна, причем указанные измерение расстояния и отображение активируют посредством компьютерной системы (20) аэропорта или вручную и принимают посредством антенны (16) передаваемую воздушным судном (5) информацию (17), отличающийся тем, что из указанной информации (17) извлекают, по меньшей мере, опознавательный код воздушного судна ...

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20-08-2009 дата публикации

УСТРОЙСТВО ДЛЯ ПРЕДОТВРАЩЕНИЯ ВЫКАТЫВАНИЯ ВОЗДУШНЫХ СУДОВ ЗА ПРЕДЕЛЫ ВЗЛЕТНО-ПОСАДОЧНОЙ ПОЛОСЫ

Номер: RU2008104973A
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Устройство для предотвращения выкатывания воздушных судов (ВС) за пределы взлетно-посадочной полосы (ВПП), содержащее систему определения местоположения ВС, выполненную в виде навигационной системы в комбинации с приемником спутниковой навигационной системы, систему сигнализации, базу данных, содержащую информацию относительно взлетно-посадочной полосы и связанных с ней процедур, и ЭВМ, отличающееся тем, что устройство снабжено блоком связи с бортовым оборудованием, блоком управления механизмом блокировки рычага управления реверсом тяги и блоком связи с автоматом управления тягой, причем в упомянутую ЭВМ введены блок вычисления текущего отрицательного ускорения и потребной для остановки дистанции для текущих значений скорости и ускорения, соединенный на входе с блоком связи с бортовым оборудованием, блок расчета фактической дистанции до торца ВПП и сравнения ее с потребной для остановки дистанцией, соединенный с блоком вычисления текущего отрицательного ускорения и потребной для остановки ...

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20-06-2015 дата публикации

СПОСОБ КОНТРОЛЯ ПАРАМЕТРОВ ПОЛЕТА НАЗЕМНЫМ РЕГИСТРАТОРОМ

Номер: RU2013154666A
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Способ контроля параметров полета наземным регистратором, состоящим из передачи видеоизображения приборной доски самолета на командный пункт управления, причем передача видеосигнала и управление самолетом осуществляют на заранее выделенных и зарегистрированных радиочастотах, отличающийся тем, что в кабине пилотов на бортовом держателе жестко устанавливают смартфон таким образом, чтобы его объектив обеспечивал на экране смартфона изображение приборной доски, положение командно-контрольных органов самолета, а также положение и действие пилотов, кроме того, для регистрации речевой информации экипажа используют микрофон смартфона, одновременно видео и звуковой сигналы со смартфона передают с помощью спутниковой, сотовой мобильной связи на наземный регистратор, где осуществляют видео- и аудиозапись параметров полета от взлета до посадки самолета, затем видео- и аудиозаписи наземного регистратора используют для технического анализа результатов полета в случае аварийной ситуации или поиска самолета ...

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02-10-2024 дата публикации

Бортовая система индивидуальной защиты летательного аппарата от поражающего воздействия переносных зенитно-ракетных комплексов

Номер: RU228084U9

Полезная модель относится к бортовым системам индивидуальной защиты (СИЗ) летательного аппарата (ЛА) от поражающего воздействия переносных зенитно-ракетных комплексов (ПЗРК), оснащенных управляемой ракетой (УР) с инфракрасной (ПК) головкой самонаведения (ГСН) и тепловизионным прицелом (ТВП) в составе оптико-визуального тракта (ОВТ) управления наведением ПЗРК на цель. В СИЗ ЛА реализован секторный принцип построения зоны защиты ЛА посредством постановки активной помехи (АП), формируемой группой установленных неподвижно относительно корпуса ЛА, идентичных по светотехническим характеристикам направленных излучателей модулированного по амплитуде некогерентного ИК-излучения в спектральном диапазоне 3,0-5,0 мкм, совокупная индикатриса которых перекрывает по азимуту и углу места зону защиты ЛА. Особенность конструкции предлагаемой СИЗ ЛА состоит в том, что каждый из образующих группу направленных излучателей выполнен с возможностью функционирования в двух режимах - формирование имитирующей АП ...

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20-07-2008 дата публикации

УСТРОЙСТВО ДЛЯ ОБЕЗВРЕЖИВАНИЯ ТЕРРОРИСТОВ В ГРАЖДАНСКИХ САМОЛЕТАХ

Номер: RU2007100825A
Принадлежит:

Устройство для обезвреживания террористов в гражданских самолетах, включающее салон самолета с рядами пассажирских кресел, образующих ограниченный боковинами кресел проход к кабине пилотов, отличающееся тем, что салон снабжен видеокамерой общего обзора, каждая пара расположенных напротив друг друга по разные стороны от прохода боковин кресел снабжена упругими зажимами, выполненными в виде заармированных в твердую резину алюминиевых дугообразных пластин, прикрепленных к боковинам зафиксированными в сжатом состоянии цилиндрическими пружинами, а также фотоэлектронными датчиками, фиксаторы пружин соединены с подвижными сердечниками размещенных под соответствующим креслом электромагнитов, при этом обмотки возбуждения электромагнитов электрически подключены к цепи фотоэлектронных датчиков, а пластины зажимов соединены с источниками электрического сигнала с помощью соответствующих данной паре кресел переключателей и кнопок включения ручного/автоматического режимов на специальном пульте в кабине ...

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27-01-2011 дата публикации

СПОСОБ ОБНАРУЖЕНИЯ МЕСТА АВАРИИ ЛЕТАТЕЛЬНОГО АППАРАТА, ОБЕСПЕЧЕНИЯ ЗАЩИТЫ ОТ ПОВРЕЖДЕНИЙ ЕГО БОРТОВЫХ ЗАЩИЩЕННЫХ НАКОПИТЕЛЕЙ И СОЗДАНИЯ СВОБОДНОГО ДОСТУПА К МЕСТУ ИХ АВАРИЙНОГО РАСПОЛОЖЕНИЯ

Номер: RU2009128541A
Принадлежит:

... 1. Способ обнаружения места аварии летательного аппарата, обеспечения защиты от повреждений его бортовых защищенных накопителей и создания свободного доступа к месту их аварийного расположения, в котором несколько или один бортовой защищенный накопитель монтируют внутри фюзеляжа или в других элементах конструкции летательного аппарата и устанавливают его в качестве быстросъемного элемента, включающего функцию спускаемого модуля, бортовой накопитель оснащают одним из двух существующих на техническом уровне парашютирующих устройств, которые выполняют или из мягких материалов, в виде парашюта, включающего купол с комплектом строп, или из твердых материалов, в виде несущего или воздушного винта, включающего систему складывания лопастей, в купол парашюта или в лопасти винта включают легкие материалы, придающие их устройствам положительную плавучесть, или создают положительную плавучесть, включая в их устройство пустотелые, водонепроницаемые, наполняемые воздухом или иным газом карманы, после ...

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22-11-1990 дата публикации

Providing view from high performance aircraft - involves hinged external mirror and fixed internal mirror

Номер: DE0004016096A1
Принадлежит:

The device provides a crew of a high performance aircraft with a better view of the surroundings during take-off and landing. It incorporates an external mirror (12) which can be adjusted in its angular position or lie flat against the outside skin of the aircraft. The mirror is mounted over a transparent region of the aircraft skin and reflects light onto a fixed internal mirror. This internal mirror reflects the light to the pilot's eyes so that the pilot's view corresponds to that from a point outside the aircraft. USE - High performance aircraft. Periscope system to assist in takeoff and landing.

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13-04-2006 дата публикации

Verfahren und Einrichtung zur Feststellung der Emission einer hochfrequenter elektromagnetischen Störstrahlung innerhalb des Innenraums einer für elektromagnetische Strahlung überwiegend schlecht durchlässigen Luftfahrzeughülle

Номер: DE0019704763B4
Принадлежит: PLATH GMBH

Verfahren zur Feststellung der Emission einer hochfrequenten elektromagnetischen Störstrahlung innerhalb des Innenraums einer für elektromagnetische Strahlung überwiegend schlecht durchlässigen Luftfahrzeughülle (3), dadurch gekennzeichnet, daß die elektromagnetische Strahlung in wenigstens einem vorgebbaren Frequenzbereich innerhalb der Luftfahrzeughülle mit wenigstens einem Innensensor (2) erfaßt wird, daß die elektromagnetische Strahlung in dem vorgebbaren Frequenzbereich außerhalb der Luftfahrzeughülle mit wenigstens einem Außensensor (1) erfaßt wird, in welchem Frequenzbereich eine intensive Störstrahlung durch Mobilfunktelefonsysteme und/oder Displayablenk- und Abtast-, Takt- oder Fernsteuerfrequenzen sowie deren Oberwellen und Interferenzen von elektronischen Geräten, Spielzeugen und Computern erfolgt und/oder in welchem eine erhöhte Sensibilität für den Flugzeugbetrieb notwendigen elektronischen Einrichtungen und der Flugfunk- und/oder der Navigationseinrichtungen vorliegt, daß ...

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13-08-1998 дата публикации

Method and equipment for detecting h.f. electromagnetic interference radiation from passenger section of plane

Номер: DE0019704763A1
Принадлежит:

The method involves detecting the electromagnetic radiation outside the plane hull (3) with at least one external sensor (1) and that from within the hull with at least one internal sensor (2). The outputs of the two sensors are compared and a comparative value is obtained. This comparison value is used to determine if disturbance radiation is present and to provide an appropriate alarm signal. The detection can relate to at least one specific frequency range. This can be that frequency range to which the aircraft radio and/or navigation systems are most sensitive ...

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09-11-2017 дата публикации

Verfahren und System zur Lokalisierung einer Störstrahlungsquelle in einem Innenraum eines Fahrzeugs

Номер: DE102016005349A1
Принадлежит:

Bei einem erfindungsgemäßen Verfahren zur Lokalisierung einer Störstrahlungsquelle in einem Innenraum eines Fahrzeugs, insbesondere in einer Passagierkabine (1) eines Luftfahrzeugs, wird in einer Kalibriermessung für mindestens zwei an unterschiedlichen Positionen in dem Innenraum angeordnete Funkempfänger jeweils mindestens ein Kalibrierfeld ermittelt, das bei mindestens einer Frequenz (fi) eine Felddämpfung zwischen einer Mehrzahl von Orten (x, y) innerhalb des Innenraums und dem jeweiligen Funkempfänger darstellt, und die ermittelten mindestens zwei Kalibrierfelder werden gespeichert. Beim Betrieb des Fahrzeugs wird mit den mindestens zwei Funkempfängern eine Amplitude einer Störstrahlung bei der mindestens einen Frequenz (fi) gemessen und aus den mit den mindestens zwei Funkempfängern gemessenen Amplituden der Störstrahlung mittels der gespeicherten Kalibrierfelder ein Ort (xs, ys) der Störstrahlungsquelle ermittelt. Die Erfindung betrifft auch ein System zur Lokalisierung einer Störstrahlungsquelle ...

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08-01-1998 дата публикации

Allwetterbezug für Flugzeuge, Kinderwagen, Maschinen u.a.

Номер: DE0029705455U1
Автор:

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07-08-2008 дата публикации

APPARAT ZUR ÜBERWACHUNG EINER FLUGZEUGKLAPPE UNTER VERWENDUNG EINES KRAFTMESSDORNS

Номер: DE0060317202T2
Принадлежит: FGP INSTRUMENTATION

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09-02-1961 дата публикации

Warneinrichtung fuer Luftfahrzeuge

Номер: DE0001099363B
Принадлежит: BENDIX CORP, THE BENDIX CORPORATION

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02-11-1989 дата публикации

Launched net in order to allow police or military forces to operate on the smooth outer walls of aircraft

Номер: DE0003813810A1
Принадлежит:

An air-transportable launched net has been invented which enables police or military operational forces to operate on the smooth outer wall of aircraft in order to penetrate into the interior of aircraft or carry out diversionary measures without having to make use of any ground-assisted aids. However, by means of this invention it is also possible to consider openings which previously could not be reached.

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23-03-1972 дата публикации

Номер: DE0002047109A1
Автор:
Принадлежит:

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03-04-2003 дата публикации

Security and skyjacking prevention system for large aircraft includes identification circuit for recognition of crew members and to disable flight controls if handled by skyjacker

Номер: DE0010150661A1
Принадлежит:

The aircraft has manual controls (5) and an autopilot (11) connected (6) to a switching circuit (7). A radio control circuit (13) is connected to an antenna which can receive flight control signals from ground control. There is a crew member authentification circuit (2) which must receive a password from each crew member before touching the controls, with a connection to the switching circuit (8). The switching circuit is connected to a control circuit (1) with a keyboard (3) for input of personal data.

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02-02-2012 дата публикации

Cockpit for airplane, has swinging door, hinge and area for covering angular point of door, where airplane cockpit personnel is set in cockpit area

Номер: DE102010032493A1
Принадлежит:

The cockpit has a swinging door (5), a hinge (4) and an area for covering an angular point of the door. The airplane cockpit personnel is set in a cockpit area (1) and the passengers are set in a rear area (3) of an airplane.

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04-10-1979 дата публикации

Номер: DE0002353831C3

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19-08-2010 дата публикации

Vorrichtung zur Übermittlung von Information betreffend einen Betriebszustand eines Fahrzeugs

Номер: DE102009006830A1
Принадлежит:

Eine Vorrichtung zur Übermittlung von Information, betreffend einen Betriebszustand eines Fahrzeugs, insbesondere eines Luft- oder Raumfahrzeugs, wobei die Vorrichtung als Information taktile Reize mittels eines Reizerzeugers (2; 20) auf zumindest eine Bedienperson des Fahrzeugs ausübt, zeichnet sich dadurch aus, dass die Reizausübung auf ein Sinnesorgan oder ein Körperteil der Bedienperson erfolgt, das während des störungsfreien und ordnungsgemäßen Betriebs des Fahrzeugs nicht zur aktiven Informationsübermittlung genutzt wird.

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14-08-1996 дата публикации

Defeating plane hijackers

Номер: DE0019504084A1
Автор: NICHTNENNUNG
Принадлежит:

After the introduction of such material all people, including the perpetrators or hijackers, are perforce, out of action, so that the aircraft can be stormed without shooting or without force and taken under control and the offenders disarmed and arrested, all without bloodshed. The officers or soldiers entering the cabins can use gas masks or breathing equipment to protect themselves against the anaesthetic, and the material used has to be reliable, effective, knocking out the hijackers, all of them, quickly and completely. It must not harm the officers using it, on the other hand. Laughing gas is a possible substance. The introduction of the gas is remotely controlled once the aircraft is at a standstill. The signal is then transmitted to outside to indicate that the process of the injection of gas has been started.

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15-09-2005 дата публикации

Glider thermal source location procedure analyses flight data updated from central databank and displays upcurrent predictions to pilot

Номер: DE102004009776A1
Принадлежит:

A glider thermal source location procedure analyses (9) flight data from a data bank updated with zone data from a central data bank (17) with current data using GPS (Global Positioning System) (21) and weather forecast (22) as a knowledge basis to locate potential upcurrents and display (19) the information to the pilot.

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12-06-1922 дата публикации

Ruderlagenanzeiger

Номер: DE0000354554C
Автор:

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12-07-2012 дата публикации

Stabilisierungseinrichtung

Номер: DE102010023228B4

Stabilisierungseinrichtung für Drehflügler (11), die eine vom Drehflügler (11) in Richtung Erdboden an mindestens einem Tragseil (13) hängende Außenlast (12) tragen, wobei die Stabilisierungseinrichtung zum Generieren von auf Steuersignale zur Flugsteuerung des Drehflüglers (11) aufprägbaren Regelsignalen (R) eingerichtet ist und mindestens eine Lastpendelerfassungseinheit (S2) aufweist, die zur Erfassung der Pendelbewegung (15, 31, 41) der Außenlast eingerichtet ist, dadurch gekennzeichnet, dass die Stabilisierungseinrichtung eine Bewegungsraumermittlungseinheit (S3) aufweist, die zur Ermittlung eines freien Bewegungsraumes, in dem sich der Drehflügler (11) mit Außenlast (12) kollisionsfrei bewegen kann, eingerichtet ist, und die Stabilisierungseinrichtung zum Generieren der Regelsignale (R) in Abhängigkeit von der erfassten Pendelbewegung (15, 31, 41) der Außenlast (12) und in Abhängigkeit von dem ermittelten Bewegungsraum eingerichtet ist, um ein Aufschwingen der Außenlast und Kollisionen ...

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07-03-1941 дата публикации

laufwerkes von Bordmessinstrumenten an Luftfahrzeugen

Номер: DE0000703378C
Автор:
Принадлежит: WILH LAMBRECHT FA, FIRMA WILH. LAMBRECHT

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16-08-1979 дата публикации

TARNUNG FUER FAHR- ODER FLUGZEUGE

Номер: DE0002805864A1
Принадлежит:

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11-12-1980 дата публикации

AIRPLANE ANGLE OF ATTACK AND DIRECTION OF FLIGHT INDICATOR

Номер: DE0002941736A1
Автор: TOWNSEND R, VANDEWEGE O
Принадлежит:

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23-02-2017 дата публикации

Verfahren und System zur Detektion und ldentifikation eines vollständigen Verlusts der Steuerwirksamkeit einer Stellfläche in einem Flugsteuerungssystem eines Luftfahrzeugs

Номер: DE102013009813B4

Verfahren zur Detektion und Identifikation eines vollständigen Verlusts der Steuerwirksamkeit einer aerodynamischen Stellfläche eines Flugsteuerungssystems eines Luftfahrzeugs, bei dem von einer Steuervorrichtung ein Steuersignal uc(t) erzeugt wird, das einen Aktuator veranlasst, einen mechanischen Aktuatorzustand u(t) einzunehmen, und der Aktuator zur Bewegung der Stellfläche über eine mechanische Verbindung mit der Stellfläche verbunden ist, wobei die Detektion des Verlusts der Steuerwirksamkeit der aerodynamischen Stellfläche folgende Schritte umfasst: 1.1. auf Basis des Steuersignals uc(t) und des Aktuatorzustands u(t) unter Berücksichtigung eines Modells, das den Aktuator und eine Dynamik der Stellfläche beschreibt, Ermitteln (101) eines Residuums r(t), 1.2. Ermitteln (102) eines Signals θr(t) als eine Näherung einer Signalnorm von r(t), 1.3. Vergleichen (103) des Signals θr(t) mit einem ersten Grenzwert τ1, wobei ein Verlust der Steuerwirksamkeit der aerodynamischen Stellfläche zu ...

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22-10-2015 дата публикации

Vorrichtung zum Auffinden eines Flugschreibers

Номер: DE102014005878A1
Принадлежит:

Die Erfindung betrifft eine Vorrichtung zum Auffinden eines Flugschreibers eines havarierten Flugzeuges und des Flugzeuges selbst, wobei ein aufschwimmbarer Körper, der im Flugzeug mit geführt und im Havarierfall aus dem Flugzeug ausgestoßen wird, zum Einsatz kommt und der über Signalmittel zur Positionsanzeige verfügt. Der aufschwimmbare Körper bleibt durch ein abwickelbares Seil mit dem havarierten Flugzeug verbunden, wobei das Seil entweder im Flugzeug oder im aufschwimmbaren Körper angeordnet ist.

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17-12-2015 дата публикации

Verfahren und Vorrichtung zur Erhöhung der Flugsicherheit

Номер: DE102014008788A1
Принадлежит:

Die Erfindung betrifft ein Verfahren zur Erhöhung der Flugsicherheit durch Nutzung eines Autopiloten. Die Gesundheitsparameter der Piloten werden aktuell gemessen und einem Sollwertvergleich unterzogen und/oder die aktuell im Flugschreiber erfassten Flugdaten werden mit gespeicherten Daten über die Flugroute abgeglichen, die Daten und/oder das Ergebnis des jeweiligen Datenabgleich werden einer Bodenstation übermittelt und im Falle unzulässiger Datenabweichungen wird automatisch oder durch die Bodenstation die Flugsteuerung auf dem Autopiloten umgeschaltet.

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11-09-2014 дата публикации

Vorrichtung zur Erhöhung der Flugsicherheit

Номер: DE202014004928U1
Автор:
Принадлежит: Lange

Vorrichtung zur Erhöhung der Flugsicherheit unter Verwendung eines Flugschreibers und/oder unter Verwendung von mindestens einer Messeinrichtung für Gesundheitsdaten des Piloten, und deren Abgleich mit vorgegebenen Gesundheitsdaten in einem Vergleicher, dadurch gekennzeichnet, dass im Flugschreiber (1) die Flugroute mit zulässigen Abweichungen datentechnisch gespeichert ist und die vom Flugschreiber (1) aktuell erfassten Flugdaten durch einen Vergleicher (8) mit den abgespeicherten Flugroutendaten abgleichbar sind, wobei der Vergleicher (8) Bestandteile einer Bodenstation (4) ist, die vom Flugschreiber (1) die aktuellen Flugdaten automatisch funktechnisch übermittelt bekommt oder der Vergleicher (8) Bestandteil des Flugschreibers (1) ist und unzulässige Abweichungen zwischen den gespeicherten und den Istflugdaten an die Bodenstation (4) automatisch funktechnisch übermittelbar sind und/oder der Vergleicher (8) Bestandteil einer Bodenstation (4) ist, die von der mindestens einen Messeinrichtung ...

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27-03-2008 дата публикации

VERSTÄRKTE TÜR

Номер: DE602005004791D1
Принадлежит: AIRBUS

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22-07-1971 дата публикации

Vorrichtung zur Anzeige der Schwerpunktslage eines Luftfahrzeugs in Abhaengigkeit von Kraftstoffverbrauch

Номер: DE0001648485A1
Принадлежит:

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18-10-1979 дата публикации

Номер: DE0001675557B2

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02-04-1970 дата публикации

Flugzeug mit Schubtriebwerken

Номер: DE0001756535A1
Принадлежит:

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30-09-2010 дата публикации

Feuerlöscheinrichtung

Номер: DE0010361020B4
Принадлежит: AIRBUS GMBH, AIRBUS DEUTSCHLAND GMBH

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17-10-2002 дата публикации

Reinforcement unit, for strengthening structural component, is used with pseudo-plastic and shape-memory material, and is activated on damage or overload occurring during from martensitic to austenitic condition

Номер: DE0010106735C1

Reinforcement unit (1) is used with a pseudo-plastic shape-memory material (2). The unit is activated on damage or overload at the structural component, when the shape-memory material changes from a martensitic to an austenitic condition. The reinforcement unit can be activated by heat.

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24-04-2003 дата публикации

New type of system for anti-terror flight safety has a monitoring component, a combating component and an external aircraft control i.e. a remote control component

Номер: DE0010146880A1
Автор: NACHTRÄGLICH
Принадлежит:

When fitted with a new type of anti-terror flight safety system, an aircraft's flight safety cannot be impaired through an unexpected takeover for the purpose of a terrorist attack or hijack. A safety system has three components: a monitoring component, a combating component and an external aircraft control i.e. a remote control component.

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04-03-1964 дата публикации

Integrated flight instrument system

Номер: GB0000951444A
Автор:
Принадлежит:

... 951,444. Aircraft instruments; Mach number meters. KOLLSMAN INSTRUMENT CORPORATION. May 2, 1960 [May 6, 1959], No.41091/63. Divided out of 951,441. Headings G1L and G1N. The description is identical with that of Specification 951, 441 but the claims relate to the system of comparing the correcting signals generated by the primary and duplicate instrument computers to give a warning of inaccuracy in either computer. Specification 951, 443 also is referred to.

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19-06-2013 дата публикации

A method and apparatus for transmitting data from an aircraft after detection of an undesirable condition

Номер: GB0002497674A
Принадлежит:

An aircraft flight data transmitter 118 is configured to be connected to a connector 120 of an on-board flight data recorder (FDR) system 104 in an aircraft. The aircraft flight data transmitter receives data generated by sensors 112 in the aircraft from the on-board FDR system. The aircraft flight data transmitter determines whether an undesired condition 142 is present in the aircraft using the data. The aircraft flight data transmitter initiates sending of a portion of the data received from the on-board FDR system over a wireless communications link 144 in response to a determination that an undesired condition is present in the aircraft. The connector used to connect the aircraft flight data transmitter to the on-board FDR system may be the test connector 126 of the on-board FDR system. The aircraft flight data transmitter may receive power through the connector and may be connected to the primary power bus 132. The aircraft flight data transmitter may provide power to the antenna ...

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07-08-1919 дата публикации

Improvements in Anti-vibration Supports or Suspensions.

Номер: GB0000130413A
Принадлежит:

... 130,413. Horsfield, C. Feb. 19, 1918. Cases, clock. - An anti-vibration suspension device for supporting chronometers &c. on ships, comprises elastic cords held rigidly at their upper and lower ends and pivotally and detachably connected at their middle points to the chronometer &c. case. The cords Q are fixed to arms M, N of two brackets J by threading them through holes or notches P, R. At substantially the midpoints of the vertical portions of the cords Q they are threaded through holes in loose buckles T and around pins U secured by brackets V to the suspended article. The brackets J may be placed horizontally, and three articles may be suspended side by side by the use of two pairs of brackets.

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18-08-2004 дата публикации

Aircraft takeoff

Номер: GB0000415618D0
Автор:
Принадлежит:

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31-12-1970 дата публикации

RECORDER

Номер: GB0001217668A
Принадлежит:

... 1,217,668. Tape recorders. A. & M. FELL (MFG.) Ltd. 19 Feb., 1969, No. 8896/69. Heading G5R. A flight recorder comprises a curved, e.g. spherical, rigid enclosure 2, 3 containing in its central region a platform 5 having mounted on its opposite sides respectively two recording systems 13, 14 which are driven at different speeds by a single electric motor 10, mounted on the platform 5, through a drive transmission system 12 mounted inside the platform. The enclosure is formed by an inner steel shell 1, a layer of thermal insulation 6, and a titanium outer shell 4. One recording system 13 is used for data and may be of the type described in Specifications 1,217,667 and 1,217,669 while the second recording system 14 is used for speech.

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12-06-1974 дата публикации

SYSTEM FOR USE IN CONDUCTING AIRCRAFT CHECK LISTS

Номер: GB0001356075A
Автор:
Принадлежит:

... 1356075 Aircraft cockpit check-list apparatus C B DICKINSON 24 Nov 1972 54410/72 Heading B7W A system for facilitating the performing by a pilot in an aircraft of routine and emergency check lists comprises tape recording apparatus and a cockpit-mounted speaker for playing tapes pre-recorded with said routine and emergency check lists. A pilot-actuatable control panel, Fig. 1, comprises on/off switch 11 which also includes a deferred-item position, a start-reply bar 12 which controls a switch spring-biased to an open position, an item-repeat push button switch 13, also spring biased to open position, a manual reset push button switch 14, a volume control knob 15 and a selector switch 16 whereby a desired pre-recorded message may be selected, an indication of the selected message being displayed in a window 17. The pre-recorded messages may enumerate pre-flight or in-flight checks to be made by the pilot and these would be selectable by switch 16. Other messages would issue duties to be ...

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12-06-1974 дата публикации

FLIGHT DATA ACQUISITION AND RECORDING SYSTEMS

Номер: GB0001356109A
Автор:
Принадлежит:

... 1356109 Magnetic recording apparatus SPERRY RAND Ltd 25 Aug 1971 [26 Aug 1970 41019/70 Heading G5R A flight recording system has a recorder unit 1 which is detachable from the remainder of the system and which comprises a easing 4 in which is mounted a tape deck 5, a drive motor 108 for the tape deck 5 being external to the recorder unit 1 and being disconnectible from the tape deck 5, the motor 108 driving a belt 116 which is engaged by a pulley 76 on a drive shaft 61, Fig. 2, extending through the tape deck casing 4, when the unit 1 is positioned in the system. The belt 116 is tensioned around pulleys 118, 119 by a pivoted, counterbalanced arm 121. The recorder unit 1 includes two coaxial spools 21, 22 carrying a six-track tape 23. Nylon tape-guide rollers 24-26 are barrel-shaped and are inclined to the base 14 of the tape deck 5. Four further rollers 44 guide the tape 23 across three six-track heads 41, 42, 43 which successively erase, record and monitor signals. The tape 23 is driven ...

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16-07-1975 дата публикации

CONTROL SYSTEM FOR PREVENTING MISSILES OR AIRCRAFT FROM STALLING

Номер: GB0001400228A
Автор:
Принадлежит:

... 1400228 Controlling aircraft MESSERSCHMITT-BOLKOW-BLOHM GmbH 12 Dec 1972 [16 Dec 1971] 57209/72 Heading B7G An apparatus for preventing pitching-up into a stalled condition of an aircraft or an airborne missile having a movable control surface, e.g. an elevator, comprises a first means for detecting the instantaneous angle of attack of the aircraft or missile, a second means for detecting the rate of change of said angle of attack in response to a change in control surface position and control means which defines a permissable angle of attack for stopping the control surface movement in response to said first and second means whereby said control surface movement is stopped in advance of the aircraft or missile reaching said permissible angle of attack.

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28-03-2013 дата публикации

AVIONICS CONTROL AND DISPLAY UNIT

Номер: US20130076540A1
Принадлежит: GARMIN INTERNATIONAL, INC.

A multi-product avionics control and display unit (CDU). In implementations, the CDU may include a display and a processor coupled with the display. The processor is configurable to operate in a first mode to cause the display to present standby primary flight information associated with the aircraft and a second mode to control and display operation of one or more aircraft systems associated with the aircraft. 1. An avionics control and display unit (CDU) for use in an aircraft , the CDU comprising:a switch;a display;one or more memories operable to store an avionic controller module and a primary flight mode module; and operate in a first mode to execute the primary flight mode module to cause the display to present standby primary flight information associated with the aircraft, and', 'operate in a second mode to execute the avionic controller module to control and display operation of one or more aircraft systems associated with the aircraft,, 'one or more processors coupled with the switch, the display, and the one or more memories, one or more of the processors being configurable towherein the one or more processors default to operation in the first mode after activation of the switch.2. The CDU of claim 1 , wherein the primary flight mode module is provided by a first software image and the avionic controller module is provided by a second software image claim 1 , wherein the software images do not depend on an underlying operating system external to the images for execution.3. The CDU of claim 1 , wherein the display presents a graphical user interface that includes standby primary flight information when the processor is operating in the first mode.4. The CDU of claim 1 , wherein the display includes a touch interface operable to allow selection of one or more indicia displayed by the display to control and display information about the one or more systems of the aircraft when the processor is operating in the second mode.5. The CDU of claim 1 , wherein the ...

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18-04-2013 дата публикации

Ejection Device for a Flight Data Recorder

Номер: US20130092795A1
Принадлежит: EADS DEUTSCHLAND GmbH

An ejection device for a flight data recorder includes an ejection spindle, which can be detachably connected to the flight data recorder by means of a bayonet coupling. The bayonet coupling can be released by means of force application by the ejection spindle, a disengaging device, which has a compression-resistant housing and into which the ejection spindle can be screwed, and a gas pressure generator, a valve, which is located within the disengaging device and which permits a flow connection between the outlet of the gas pressure generator and the ejection spindle when the ejection spindle is screwed in and which disables the flow connection between the outlet of the gas pressure generator and the ejection spindle when the ejection spindle is unscrewed. 13-. (canceled)4. An ejection device for a flight data recorder , withan ejection spindle configured to be releasably connected to the flight data recorder via a bayonet fastening, wherein the bayonet fastening is configured to be releasable by being acted upon by the ejection spindle;a disengagement device with a gas pressure generator and a pressure-resistant housing, wherein the ejection spindle is screwable into disengagement device; and permit a flow connection between an outlet of the gas pressure generator and the ejection spindle when the ejection spindle is screwed into the disengagement device, and', 'prevent the flow connection between the outlet of the gas pressure generator and the ejection spindle when the ejection spindle is not screw into the disengagement device., 'a valve arranged inside the disengagement device and which is configured to'}5. The ejection device as claimed in claim 4 , wherein the valve is configured to be prestressed by the ejection spindle being screwed into the disengagement device.6. The ejection device as claimed in claim 4 , wherein the ejection spindle comprises a spindle rod claim 4 , which is configured to be movable by gas pressure claim 4 , for acting upon the bayonet ...

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18-04-2013 дата публикации

DISPLAY APPARATUS, CONTROL SUPPORT SYSTEM, AND DISPLAY METHOD

Номер: US20130096738A1
Автор: YAMASAKI Koichi
Принадлежит:

An FPM and a target attitude relative to air display are displayed on a PFD, which is an integrated indicator. The target attitude relative to air display is a mark indicating a target attitude relative to air representing a target angle-of-attack and a target sideslip angle of the aircraft to achieve a target flight path. The PFD displays the relative difference between the FPM and the target attitude relative to air display and shows that the aircraft is flying in the target traveling direction when the FPM matches (is superposed on) the target attitude relative to air display. Thus, controlling with higher trackability than controlling performed based on a target attitude relative to ground is enabled. 1. A display apparatus that displays a flying situation of an airplane , which is an aircraft ,wherein the display apparatus displays a relative difference between a target attitude relative to air, representing a target angle-of-attack and a target sideslip angle of the aircraft to achieve a target flight path, and a current attitude relative to air, representing a current angle-of-attack and a current sideslip angle of the aircraft.2. A display apparatus according to claim 1 ,wherein the target angle-of-attack is derived by subtracting an angle between a horizontal plane and a target traveling direction from a current pitch angle of the aircraft; andthe target sideslip angle is derived by subtracting a current direction angle of the aircraft from an direction angle of the target traveling direction.3. A display apparatus according to claim 1 , wherein a first mark corresponding to the target attitude relative to air and a second mark corresponding to the current attitude relative to air are displayed.4. A display apparatus according to claim 3 , wherein the relative positions of the first mark and the second mark are displayed while being changed according to the relative difference between the target attitude relative to air and the current attitude relative to ...

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02-05-2013 дата публикации

Particle sensor for in situ atmospheric measurement

Номер: US20130110326A1
Автор: Roland Kelm
Принадлежит: AIRBUS OPERATIONS GMBH

A measuring device for an aircraft is provided in order to determine physical properties of aerosol particles in real time. The device includes a heating device that separates volatile and solid aerosol particles, and a particle sensor that measures acquired data. The physical properties of the solid aerosol particles are determined with an analyzer. The determined analytical data is forwarded to other internal aircraft systems via a communication interface. Due to the formation of a measuring data or analytical data network with several airliners equipped with the measuring device, accurate and up-to-date information on the particle pollution, for example, along flight paths, can be obtained and used for defining no-fly zones, if so required.

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16-05-2013 дата публикации

PROTECTION DEVICE FOR SENSITIVE AREAS AGAINST IMPACT OF FOREIGN OBJECTS

Номер: US20130119201A1
Принадлежит: AIRBUS OPERATIONS, S.L.

A protection device includes a flexible laminar body resistant to impacts, arranged separately from the body to be protected and put in the way of the beam of possible trajectories with which a foreign object could impact on the object to be protected, and it includes a plurality of energy absorption elements, provided with device clamping elements over a support structure positioned outside of the beam of possible trajectories, in order for the flexible laminar body to intercept an impact trajectory by the foreign object, resulting in its deformation and the subsequent progressive extension of the energy absorption elements reducing the loads to be supported by the support structure. The protection device is applied to prevent birds or other objects from impacting on sensitive areas of aircraft. The protection device is of a textile nature of reduced weight. 110-. (canceled)11. A protection device for sensitive areas against impact of foreign objects , said device comprising:a flexible laminar body made of a material resistant to impacts, said body being arranged separately from an object to be protected and put in the way of a beam of possible trajectories with which a foreign object could impact over said object to be protected,wherein said body includes a plurality of energy absorption elements selected among textile, mechanical and hydraulic elements, such that the energy absorption elements of a textile nature, are strips, each one of which is constituted by segments superimposed in zigzag and clamped to a side of the flexible laminar body and towards its interior, said strips being provided with seals that are progressively broken when an impact of the foreign object on the flexible laminar body occurs;wherein said energy absorption elements include clamping elements on a support structure located outside the beam of possible trajectories with which the foreign object could impact the object to be protected,said energy absorption elements being configured to ...

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16-05-2013 дата публикации

METHOD AND SYSTEM FOR DISPLAYING INFORMATION ON A DISPLAY UNIT IN AN AIRCRAFT CABIN

Номер: US20130120163A1
Автор: KOLLAKOWSKI Malte
Принадлежит: AIRBUS OPERATIONS GMBH

A method and system for displaying information on an electrical display unit in an aircraft cabin including a generating unit for generating at least one signal which clearly identifies the information, a first acquiring unit for wirelessly acquiring the at least one signal and a control unit for controlling the display unit on the basis of the at least one signal. The system may also have a second acquiring unit for acquiring departure and/or arrival location information relating to a flight and a third acquiring unit for acquiring passenger information. 1. Method for displaying information on an electrical display unit in an aircraft cabin , comprisinggenerating at least one signal unambiguously identifying the information,acquiring, in particular wireless acquiring, of the at least one signal,controlling the display unit on the basis of the at least one signal,displaying the information on the electrical display unit,acquiring of at least one of departure and arrival location information of a flight anddisplaying the written information depending on the at least one of the departure and arrival location information acquired in different languages.2. Method according to claim 1 , wherein the information is written information and the display on the display unit comprisesdisplaying the written information in different languages, in particular alternating between different languages.3. Method according to claim 2 , further comprisingacquiring of passenger information anddisplaying the written information in different languages depending on the acquired passenger information.4. Method according to claim 3 , wherein the display unit is mounted on a passenger seat and the written information is displayed in different languages depending on the acquired passenger information of a passenger assigned to the passenger seat.5. Method according to claim 3 , further comprisingcontrolling of a display duration of the written information in the respective language depending on ...

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13-06-2013 дата публикации

AIRCRAFT NOSE STRUCTURE WITH LANDING GEAR COMPARTMENT

Номер: US20130146710A1
Принадлежит: AIRBUS OPERATIONS S.A.S.

An aircraft nose structure includes a fuselage and a pressuretight bulkhead fixed at its periphery to the fuselage and transversely dividing the fuselage into a pressurized upper zone and an unpressurized lower zone for accommodating retractable nose landing gear. The pressuretight bulkhead includes a floor of the pressurized upper zone, and a substantially flat rear panel extending between a rear edge of the floor and the fuselage. The floor and the rear panel are fixed laterally to the fuselage. The fuselage includes an exterior wall and reinforcing transverse frames to which the exterior wall is fixed. In line with the pressuretight bulkhead, at least some of the transverse reinforcing frames extend along the outline of the pressurized upper zone and constitute members that reinforce the pressuretight bulkhead. 1. An aircraft nose structure comprising:a fuselage; anda pressuretight bulkhead fixed at the periphery thereof to said fuselage and transversely dividing said fuselage into a pressurized upper zone and an unpressurized lower zone for accommodating retractable nose landing gear,wherein said pressuretight bulkhead comprises a floor of said pressurized upper zone, said floor being fixed laterally to said fuselage in a pressuretight manner and configured for forming a pressure barrier.2. The structure according to claim 1 , wherein said pressuretight bulkhead comprises at least one substantially flat rear panel extending between a rear edge of said floor and said fuselage.3. The structure according to claim 1 , wherein said fuselage comprises an exterior wall and a plurality of transverse reinforcing frames claim 1 , said exterior wall being fixed to the reinforcing frames claim 1 , wherein claim 1 , in line with said pressuretight bulkhead claim 1 , at least some of said transverse reinforcing frames are limited to said pressurized upper zone.4. The structure according to claim 1 , wherein at least one of the elements comprising said floor and said rear ...

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04-07-2013 дата публикации

ALARM APPARATUS FOR A PILOT'S HEADSET

Номер: US20130169451A1
Автор: Steinmetz Martin
Принадлежит: ROBERT BOSCH GMBH

The invention relates to an alarm apparatus () for a pilot's headset () and to a pilot's headset having such an alarm apparatus. The alarm apparatus comprises an attitude sensor (), which detects its inclination relative to a starting position or the horizontal, and a measuring device () for recording a period for which the inclination recorded by the attitude sensor exceeds a stipulated inclination tolerance limit. In addition, the alarm apparatus has a means () which is set up to trigger an alarm signal when a recorded period of the inclination tolerance limit being exceeded is longer than a preset maximum period. 11331. An alarm apparatus () for a pilot's headset () which has at least one earphone () , the alarm apparatus comprising:{'b': '11', 'an attitude sensor () which detects its inclination relative to a starting position;'}{'b': '12', 'a measuring device () for recording a period for which the inclination recorded by the attitude sensor exceeds a stipulated inclination tolerance limit; and'}{'b': '13', 'a computation unit () configured to trigger an alarm signal when the recorded period is longer than a preset maximum period.'}2. The alarm apparatus according to claim 1 , wherein the inclination relative to a starting position is a reference inclination or a horizontal inclination.31213. The alarm apparatus according to claim 1 , wherein the measuring device () is also set up to measure a time for which the inclination recorded by the attitude sensor does not exceed the stipulated inclination tolerance limit claim 1 , wherein the computation unit () for triggering an alarm signal is also set up to terminate a triggered alarm signal only when the inclination tolerance limit is no longer exceeded for a preset minimum period of time as a minimum time.41213. The alarm apparatus according to claim 1 , wherein the measuring device () is also set up to measure a time for which the inclination recorded by the attitude sensor does not exceed the stipulated ...

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11-07-2013 дата публикации

METHOD OF AUTOMATICALLY CONTROLLING A ROTARY WING AIRCRAFT HAVING AT LEAST ONE PROPULSION PROPELLER, AN AUTOPILOT DEVICE, AND AN AIRCRAFT

Номер: US20130175385A1
Автор: Eglin Paul
Принадлежит: EUROCOPTER

An autopilot device () and method for automatically piloting a rotary wing aircraft (), having at least one propulsion propeller (), said rotary wing comprising at least one rotor () with a plurality of blades (), said device comprising a processor unit () co-operating with at least one collective control system () for controlling the collective pitch of said blades (). The device includes engagement means () connected to the processor unit () for engaging an assisted mode of piloting for maintaining an angle of attack, said processor unit () automatically controlling the collective pitch of the blades () when the assisted mode of piloting for maintaining an angle of attack is engaged by controlling said collective control system to maintain an aerodynamic angle of attack (α) of the aircraft at a reference angle of attack (α*). 1. A method of automatically piloting a rotary wing aircraft , said aircraft having at least one propulsion propeller , said rotary wing comprising at least one rotor provided with a plurality of blades , wherein during an assisted mode of piloting for maintaining an angle of attack , the aerodynamic angle of attack (α) of the aircraft is maintained equal to a reference angle of attack (α*) by automatically controlling the collective pitch of said blades.3. A method according to claim 1 , wherein the reference angle of attack (α*) is equal to the current aerodynamic angle of attack (α) of the aircraft at the moment that the assisted mode of piloting for maintaining an angle of attack is engaged.4. A method according to claim 1 , wherein the value of the reference angle of attack (α*) is modified in flight.5. A method according to claim 1 , wherein the longitudinal attitude (θ) is automatically maintained equal to a reference longitudinal attitude (θ*) claim 1 , the current longitudinal attitude being equal to said reference attitude (θ*).6. A method according to claim 5 , wherein the reference attitude (θ*) is servo-controlled automatically ...

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18-07-2013 дата публикации

Piloting assistance method, a piloting assistance device, and an aircraft

Номер: US20130184902A1
Автор: Paul Eglin
Принадлежит: Eurocopter SA

A piloting assistance device ( 5 ) comprising a calculation unit ( 10 ) and a display unit ( 20 ). The calculation unit ( 10 ) executes stored instructions to determine at least one thrust margin for a propeller between a current thrust being exerted by said propeller and a threshold thrust corresponding to a negative power limit (Pmin), and to determine a main minimum total ground slope that can be followed by the aircraft in descent as a function of said thrust margin. Finally, the calculation unit presents a main symbol ( 25 ) on a display unit ( 20 ), the main symbol ( 25 ) representing the minimum total ground slope that can be followed by the aircraft ( 1 ) in descent, the main symbol ( 25 ) appearing superimposed on a representation ( 21 ) of the surroundings that exist in front of the aircraft ( 1 ).

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25-07-2013 дата публикации

PROTECTIVE SHIELD AGAINST ICE IMPACTS ON AIRCRAFT

Номер: US20130187002A1
Принадлежит: AIRBUS OPERATIONS, S.L.

Protective shield against ice impacts on aircraft, wherein the shield comprises plies of composite material () having microcapsules (), each microcapsule containing a healing agent (). 11225. Protective shield against ice impacts on aircraft structures characterized in that the shield comprises plies of composite material () having microcapsules () , each microcapsule () containing a healing agent ().2. Protective shield against ice impacts on aircraft structures according to claim 1 , wherein:{'b': 1', '2', '3, 'the composite material () also has microcapsules () containing catalyst particles (),'}{'b': 5', '2', '4, 'claim-text': [{'b': 2', '5, 'at least a microcapsule () with the healing agent (), and'}, {'b': 2', '3, 'at least a microcapsule () with catalyst particles (),'}], 'the healing agent () contained in a microcapsule () actuates when a crack () produced at the shield reaches{'b': 3', '5', '5', '6, 'and the catalyst particles () react with the healing agent (), such healing agent () becoming a polymerized healing agent ().'}32. Protective shield against ice impacts on aircraft structures according to any or claim 1 , wherein the microcapsules () are made of urea-formaldehyde.42. Protective shield against ice impacts on aircraft structures according to any or claim 1 , wherein the microcapsules () are made of polyvinyl alcohol.55. Protective shield against ice impacts on aircraft structures according to any previous to claim 1 , wherein the healing agent () is dicyclopentadiene.63. Protective shield against ice impacts on aircraft structures according to claim 5 , wherein the catalyst particles () are tungsten hexachloride and diethyaluminum chloride (WCl-EtAlCl) particles claim 5 , or ruthenium carbene complexes particles claim 5 , or osmiun carbene complexes particles.75. Protective shield against ice impacts on aircraft structures according to any previous to claim 5 , wherein the healing agent () is cyanoacrilate.83. Protective shield against ice ...

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25-07-2013 дата публикации

Fire protection device for aircraft

Номер: US20130187004A1
Принадлежит: EADS Construcciones Aeronauticas, S.A.

A joint attaching a structural element to a composite part comprising a metallic attachment, this joint being subjected to a fire source on one of its sides, the fire side. The joint comprises a retaining device located at the side of the joint opposite to the fire side, the cold side. The retaining device comprises a first surface that is in contact with the metallic attachment, and a second surface which is in contact with the composite part. The second surface has a larger area in contact with the composite part than the area of the first surface in contact with the metallic attachment. The retaining device is made of a material with a high thermal conductivity. Such a joint may be in an aircraft. 1. A joint attaching a structural element to a composite part comprising a metallic attachment , this joint being subjected to a fire source on one of its sides , the fire side , the joint comprising:a retaining device located at the side of the joint opposite to the fire side, the cold side,the retaining device comprising a first surface that is in contact with the metallic attachment, and a second surface which is in contact with the composite part,the second surface having a larger area in contact with the composite part than the area of the first surface which is in contact with the metallic attachment,the retaining device being made of a material with a high thermal conductivity.2. The joint according to wherein the area of the second surface in contact with the composite part is at least three times larger than the area of the first surface in contact with the metallic attachment.3. The joint according to wherein the material of the retaining device has a thermal conductivity of at least 10 W/mK.4. The joint according to wherein the composite part is designed to work under temperature conditions lower than its Glass Transition Temperature.5. The joint according to wherein an airflow is present on the cold side.6. The joint according to wherein the metallic ...

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25-07-2013 дата публикации

SYSTEM AND METHOD FOR PROVIDING AN AIRCRAFT NOISE ADVISORY DURING DEPARTURE AND ARRIVAL OF AN AIRCRAFT

Номер: US20130190950A1
Автор: SHUKLA VIJAY
Принадлежит: Airbus Engineering Centre India

A system and method for providing an aircraft noise advisory during departure and/or arrival of an aircraft are disclosed. In one embodiment, predefined allowable aircraft noise level information associated with a plurality of aircraft noise sensors located in the vicinity of airports are obtained. Further, predefined allowable aircraft noise level information associated with one or more of the plurality of aircraft noise sensors is presented on a display device in the aircraft, based on a current location of the aircraft, upon receiving noise data request from a pilot. Furthermore, current aircraft noise level information is obtained from one of the one or more aircraft noise sensors. In addition, the current aircraft noise level information is compared with predefined allowable aircraft noise level information associated with the one of the one or more aircraft noise sensors. Also, the aircraft noise advisory is displayed based on an outcome of the comparison. 1. A method for providing an aircraft noise advisory during departure and/or arrival of an aircraft , comprising:obtaining predefined allowable aircraft noise level information associated with each of a plurality of aircraft noise sensors located in the vicinity of airports;presenting predefined allowable aircraft noise level information associated with one or more of the plurality of aircraft noise sensors on a display device in the aircraft, based on a current location of the aircraft, upon receiving a noise data request from a pilot;obtaining current aircraft noise level information from one of the one or more aircraft noise sensors during the departure and/or arrival;comparing the current aircraft noise level information with predefined allowable aircraft noise level information associated with the one of the one or more aircraft noise sensors; anddisplaying the aircraft noise advisory on the display device based on an outcome of the comparison.2. The method of claim 1 , further comprising:obtaining an ...

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25-07-2013 дата публикации

Method and device for communicating true runway braking performance using data from the flight data management systems of landed aircraft

Номер: US20130190999A1
Автор: Rado Zoltan Ivan
Принадлежит: Aviation Safety Technologies, LLC

A method and apparatus for calculating a standardized value for the actual runway braking coefficient of friction of one or more arriving aircraft using data from each aircraft's flight data recorder or flight data management system, standardizing the calculated information to provide redundancy and to make it usable by subsequently arriving aircraft, and reporting the calculated standardized value information to individuals and agencies including air traffic control, airport operations and maintenance, and aircraft pilots and ground crews; and A method and apparatus for calculating the actual runway braking coefficient of friction of an aircraft using data from the aircraft's flight data recorder or flight data management system, transmitting the data in real-time to an off-aircraft high-power computing system, calculating off-aircraft the landing aircraft's actual runway braking coefficient of friction, and reporting the calculated information to individuals and agencies including air traffic control, airport operations and maintenance, and aircraft pilots and ground crews. 1. A computer network for calculating and distributing a true aircraft braking friction coefficient for an aircraft runway or taxiway comprising:(A) An aircraft having a flight data management system for recording one or more sets of data points thereon, wherein the one or more sets of data points pertain to one or more of the following aircraft properties measured at various times for the aircraft: aircraft ground speed, aircraft brake pressure, aircraft longitudinal acceleration, aircraft engine thrust setting, aircraft reverse thrust setting, aircraft engine revolutions per minute, aircraft air speed, aircraft vertical acceleration, aircraft spoiler setting, aircraft airbrake setting, aircraft aileron setting, aircraft flap configuration, aircraft pitch, and aircraft autobrake setting;(B) A computer in communication with the flight data management system of the aircraft which obtains from ...

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01-08-2013 дата публикации

Aerosol Detection

Номер: US20130193978A1
Принадлежит:

Aerosol detection apparatus comprises an aircraft having a dielectric member, such as a window (), comprised in the body () thereof such that a surface of the dielectric member forms part of the exterior surface of the aircraft. Detection means (), such as a static monitor is located on the inside of the aircraft and arranged to detect an electric field resulting from polarisation of the dielectric member. The output of the static monitor, or the rate of change thereof, correlates closely to particle density as the aircraft is flown though an aerosol, such as a volcanic ash cloud. The apparatus is simple and relatively inexpensive, and may comprise any general purpose aircraft. Aerosol particles may be detected and mapped using apparatus of the invention more easily and quickly than by use of devices such as optical spectrometers mounted on dedicated research aircraft, or static monitors mounted on the exterior of an aircraft. 115-. (canceled)16. Aerosol detection apparatus comprising an aircraft having a dielectric member comprised in a body thereof such that a surface of the dielectric member forms part of the exterior surface of the aircraft , and a sensor located in the interior of the aircraft and arranged to detect an electric field within the aircraft , the electric field resulting from the dielectric member becoming polarised so that induced charge appears on a surface of the dielectric member opposite to that forming part of the exterior surface of the aircraft.17. Apparatus according to wherein the dielectric member comprises a window of the aircraft.18. Apparatus according to claim 16 , wherein the sensor comprises a static monitor mounted within the aircraft.19. Apparatus according to wherein the static monitor comprises an electro-static voltmeter.20. Apparatus according to wherein the electro-static voltmeter comprises an electro-mechanical field mill instrument.21. Apparatus according to claim 18 , further comprising an alarm configured to generate a ...

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01-08-2013 дата публикации

METHOD FOR DETECTING PERFORMANCE OF AN AIRCRAFT BASED ON A CUSTOMIZED MESSAGE

Номер: US20130197721A1
Принадлежит: AIR CHINA LIMITED

The present invention relates to a method for detecting the performance of the aircraft comprising: collecting data reflecting operation status of the aircraft; generating the customized message based on the collected data, wherein, the customized message is configured to include one or more main parameters related to the operation status of the aircraft; storing or transmitting the customized message; and detecting the performance of the aircraft based on the customized message. 1. A method for detecting performance of an aircraft based on a customized message , comprising:collecting data reflecting operation status of the aircraft;generating the customized message based on the collected data, wherein, the customized message is configured to include one or more main parameters related to the operation status of the aircraft;storing or transmitting the customized message; anddetecting the performance of the aircraft based on the customized message.2. A method according to claim 1 , wherein claim 1 , the customized message further includes one or more auxiliary parameters related to correction of the main parameters.3. A method according to claim 2 , wherein claim 2 , the step of generating further comprising:obtaining values of the main parameters and auxiliary parameters at one or more timings in response to a trigger condition.4. A method according to claim 3 , further comprising:converting the values of the main parameters and auxiliary parameters into values under a specified condition.5. A method according to claim 4 , further comprising:correcting the values of the main parameters according to the values of the auxiliary parameters.6. A method according to claim 3 , wherein claim 3 , the main parameters of the customized message are determined by the following steps:obtaining multiple parameters related to the operation status of the aircraft;determining multiple main parameters according to respective physical implications indicated by the multiple parameters ...

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01-08-2013 дата публикации

GUST COMPENSATED TOTAL ENERGY VARIOMETERS

Номер: US20130197724A1
Автор: Ellis David Miller
Принадлежит:

Rise and fall rates for a glider are determined based on the glider's angle of attack and speed. These rise and fall rates are used to compensate a variometer so that the impact of vertical airmass flow can be used to optimize glider soaring. Altitude measurements are used to determine the glider's potential energy while velocity is used to determine the glider's kinetic energy. Total energy compensation techniques are then used to correct error calculations in the variometer. 1. A processor implemented method for analyzing motion comprising:determining a first altitude for an aircraft;calculating a potential energy for the aircraft based on the first altitude;determining a velocity for the aircraft;calculating a kinetic energy for the aircraft based on the velocity;determining a first angle for the aircraft based on pointing direction of the aircraft relative to a pitch axis for the aircraft;determining a second angle for the aircraft, relative to the pitch axis, such that when the first angle equals the second angle there is no transfer of energy between potential energy and kinetic energy; andcalculating a first altitude-change rate for the aircraft based on the velocity and a difference between the first angle and the second angle.2. The method of further comprising calculating a pitch-compensated altitude-change rate wherein the pitch-compensated altitude-change rate includes a difference between the first altitude-change rate and an altitude change rate based on changes in static pressure.3. The method of further comprising presenting the pitch-compensated altitude-change rate.4. The method of wherein the calculating of the pitch-compensated altitude-change rate is further based on an acceleration along a vertical axis of the aircraft.5. The method of wherein the acceleration is measured using an accelerometer.6. The method of wherein the velocity claim 1 , used in the calculating of the first altitude-change rate claim 1 , is modified to compensate for an ...

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01-08-2013 дата публикации

METHOD AND DEVICE FOR DISPLAYING TRIM INFORMATION ON AN AIRPLANE DURING A TAKE-OFF

Номер: US20130197726A1
Принадлежит: AIRBUS OPERATIONS (S.A.S.)

A method and device for displaying trim information on an airplane during a take-off, for determining and displaying a precise trim setpoint which enables the pilot, by following the displayed information, to carry out a manual take-off which is optimized from the performance point of view. 2. The method as claimed in claim 1 , wherein claim 1 , in the step a) claim 1 , said rotation phase is defined between the following two successive moments:the moment when the airplane which is taxiing on the ground reaches a predetermined rotation speed; andthe moment when the airplane reaches a predetermined height in relation to the ground.43. The method as claimed in claim 1 , wherein claim 1 , in the step b) claim 1 , after the rotation phase claim 1 , a nominal pitch rate order ODV which corresponds to an order of a nominal SRS-type law claim 1 , is computed repetitively and transmitted to the display screen.5. The method as claimed in claim 1 , wherein said gains are determined claim 1 , in a preliminary step claim 1 , empirically using simulations.83. The device as claimed in claim 6 , wherein said processing means also comprise third means for repetitively computing a nominal pitch rate order ODV which corresponds to an order of a nominal SRS-type law which is transmitted to the display screen after the rotation phase.9. The device as claimed in claim 6 , wherein it also comprises means for supplying the data used in the computation of the pitch rate orders.10. An airplane claim 6 , comprising a device for displaying trim information according to . The present invention relates to a method and a device for displaying trim information on an airplane, at least during a take-off phase.When an airplane is taking off, there is no operational flight director on the vertical axis, that can be used to assist a pilot during said take-off. The expression “take-off of the airplane” should be understood here to mean the travel to the take-off, the rotation phase and until power cut ...

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08-08-2013 дата публикации

SYSTEM AND METHOD FOR REAL-TIME AIRCRAFT PERFORMANCE MONITORING

Номер: US20130204469A1
Принадлежит: ROSEMOUNT AEROSPACE INC.

A computer apparatus and method to determine aircraft fuel mileage performance. The computer apparatus including a memory and a processor disposed in communication with the memory and configured to issue a plurality of instructions stored in the memory. The instructions issue signals to receive real-time aircraft data during aircraft flight and process the real-time data to determine real-time aircraft mass data. A calculation is performed to determine the real-time fuel mileage performance for the aircraft based upon determined real-time aircraft mass data. 1. An apparatus to determine aircraft fuel mileage performance , comprising:a memory; receive real-time aircraft data during aircraft flight;', 'process said real-time data to determine real-time aircraft mass data; and', 'calculate a real-time fuel mileage performance for the aircraft based upon determined aircraft mass data., 'a processor disposed in communication with said memory, and configured to issue a plurality of instructions stored in the memory, wherein the instructions issue signals to2. The system of claim 1 , further comprising aircraft sensors that transmit real-time data to said processor.3. The system of claim 1 , wherein said real-time data is selected from a group consisting of drag claim 1 , lift claim 1 , speed and altitude.4. The system of claim 3 , wherein said instructions stored in memory further causes said processor to transmit an alert signal that indicates degradation of a fuel mileage performance.5. The system of claim 3 , wherein said instructions stored in memory further causes said processor to transmit said fuel mileage performance to a cockpit of an aircraft.6. The system of claim 3 , further comprising an aircraft having an altitude and a cruise speed claim 3 , wherein said aircraft adjusts said altitude and said cruise speed based on said fuel mileage performance.7. The system of claim 3 , wherein said processor calculates said fuel mileage performance based on said aircraft ...

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15-08-2013 дата публикации

DECOMPRESSION UNIT

Номер: US20130206909A1
Принадлежит: FACC AG

A decompression unit is suitable for use in a decompression opening of a wall element of an aircraft. The unit includes a panel which can be mounted via a frame in or over the decompression opening. The panel can be moved out of the frame at a predetermined differential pressure Δp in order to open the decompression opening. In order to form a decompression unit of as simple a design as possible and with an optimum response behavior, the panel is formed by at least one hardened prepreg layer with at least one separating joint that is filled with cured resin as a predetermined breaking point. The separating joint breaks when the predetermined differential pressure is exceeded. 112-. (canceled)13. A decompression unit for a decompression opening of a wall element of an aircraft , the decompression unit comprising:a frame;a panel disposed in said frame and mounted via said frame in or on the decompression opening, said panel and said frame being configured such that said panel is moved out of said frame at a predetermined differential pressure in order to open the decompression opening;said panel being formed of at least one hardened prepreg layer with at least one closed separating joint, said separating joint being filled with cured resin and defining a predetermined breaking point, wherein said separating joint breaks when the predetermined differential pressure is exceeded and said panel is pulled out of said decompression opening when the decompression unit triggers; anda fire protection strip of a flame-retardant material disposed on a side of said panel facing the wall element.14. The decompression unit according to claim 13 , which comprises a plastic film disposed on at least one side of said at least one prepreg layer.15. The decompression unit according to claim 14 , wherein said plastic film is a polyvinyl fluoride film.16. The decompression unit according to claim 13 , which comprises a strip of an elastic material disposed arranged on a side of said panel ...

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15-08-2013 дата публикации

FORCE GENERATOR FOR MOUNTING ON A STRUCTURE

Номер: US20130211630A1
Принадлежит: EUROCOPTER DEUTSCHLAND GMBH

The invention relates to a force generator () for mounting on a structure () in order to introduce vibrational forces in a controlled manner into said structure for affecting vibrations, comprising at least one spring arm () on which a flexural arm () having an inertial mass () and extending in the direction toward the attaching point is fastened, and having at least one piezo transducer () at both ends () of the spring arm (), wherein the center of gravity of the inertial mass () is disposed in the region of the center of the spring arm (). Alternatively, two guide springs are disposed on both sides of the spring arm () parallel thereto, in order to generate a vibrational motion, wherein the fastening point of the flexural arm () comprises an unchanged orientation during the vibrational motion. 112141612182422162614261618142414. Force generator for mounting on a structure () in order to introduce vibrational forces into the structure in a controllable manner for influencing vibration , comprising at least one spring arm () having a fixed end () for fastening to the structure () , and having a vibrating end () to which an inertial mass () is fastened via a bending arm () extending in the direction of the fixed end () , at least one piezoelectric transducer () being mounted on the spring arm () for the bending deformation thereof , characterized in that at least one piezoelectric transducer () is mounted at both ends ( , ) of the spring arm () , and the center of gravity of the inertial mass () is located at the middle of the spring arm ().214. Force generator according to one of the preceding claims , characterized in that the spring arm () has a longitudinal section with a rectangular or tapered shape.3145052265052. Force generator according to claim 1 , characterized in that the spring arm () includes a center layer () and two cover layers () coupled thereto claim 1 , the piezoelectric transducers () in each case being situated between the center layer () and one ...

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15-08-2013 дата публикации

Detection of aircraft descent anomaly

Номер: US20130211632A1
Принадлежит:

An aircraft ground or sea approach anomaly detection method. The method includes the steps of characterizing a flight phase of the aircraft, determining a prohibited flight envelope, defining a set of prohibited vertical speeds of the aircraft for given altitudes in relation to the ground or the sea, as a function of the flight phase of the aircraft characterized, and detecting a ground approach anomaly of the aircraft as a function of a current vertical speed and altitude in relation to the ground or the sea of the aircraft, in relation to the prohibited flight envelope determined. 1. A method for the detection of aircraft descent anomaly , comprising the steps: detecting a position of a throttle lever of the aircraft,', 'determining the variation of a thrust parameter of the aircraft,', 'comparing the current speed of the aircraft with a minimum speed control threshold, and', 'detecting the absence of a landing runway near the aircraft,, 'characterizing a flight phase of the aircraft, said characterization comprising at least one of'}determining a prohibited flight envelope,defining a set of prohibited vertical speeds of the aircraft for given altitudes, as a function of the flight phase of the aircraft characterized, anddetecting a descent anomaly of the aircraft as a function of a current vertical speed and altitude of the aircraft, in relation to the prohibited flight envelope determined.2. The method according to claim 1 , in which the detection of the aircraft descent anomaly by the aircraft is dependent on an authorization to reduce the altitude of the aircraft.3. The method according to claim 1 , in which the prohibited flight envelope determined corresponds to an envelope claim 1 , the area of which in terms of aircraft vertical speed-altitude is larger than that of a nominal prohibited flight envelope.4. The method according to claim 1 , also comprising claim 1 , if an anomaly is detected claim 1 , a step of generating an aircraft protection order in ...

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15-08-2013 дата публикации

SENSOR FOR DETECTING HYDRAULIC LIQUIDS IN AIRCRAFT

Номер: US20130211633A1
Принадлежит: Katholieke Universiteit Leuven

The present invention relates generally to a system that monitors the condition of hydraulic systems for an aircraft or for other applications and, more particularly, to a system and method for detecting leakage within the hydraulic system aboard an aircraft. Such system is detecting hydraulic liquids by extended sensors based on the collapse of percolation conductivity (COPC) which sensors are covering an area in the aircraft. 121242. An aircraft with an improved landing or taking off security means , characterised in that the aircraft comprises a hydraulic liquid leakage monitor for detecting of aircraft hydraulic liquid leakage in situ from the aircraft hydraulic system whereby the aircraft hydraulic liquid conduit that is at least in part surrounded by a sensing means (sensing tape , sheet , fabric or coating) [] that is permeable for aircraft hydraulic liquid (such as Skydrol® 500 B) and that is coated or is winded around the hydraulic tube [] to be sensed for an hydraulic fluid escape and whereby the sensing means comprises or is impregnated with a sensing material that comprises a composite comprising at least two components. 1) particles or powder of an electrically-conductive material dispersed in 2) an matrix that is solvable to aircraft hydraulic fluid whereby the concentration , dispersity and/or orientation of the electrically-conductive particles are tailored to be in the proximity of the percolation threshold in a way that the composite itself is normally in the electrically-conductive state but has the percolation conductivity interrupted after entering of aircraft hydraulic fluid into the composite [] and further comprising electrodes [] for measuring resistance in sensing material [].2. The aircraft with aircraft hydraulic liquid leakage monitor according to claim 1 , wherein the conductivity of the sensing material is interrupted as consequence of the absorption of the aircraft hydraulic fluid into the matrix embedding the electrically-conductive ...

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15-08-2013 дата публикации

SAFE TAKEOFF MONITORING SYSTEM

Номер: US20130211636A1
Принадлежит: EMBRAER S.A.

A safe takeoff monitoring system checks the actual physical parameters of an airplane during takeoff, determines the actual takeoff weight, and warns the pilot to interrupt the takeoff if any dangerous situation is developing, before a high energy abort is necessary. 1. A safe takeoff monitoring system for an airplane , the system comprising:sensors onboard the airplane that detect parameters relating to airplane weight; and{'sub': 'R', 'an automatic processor operatively coupled to the sensors, the automatic processing system continually computing parameters including distance required for stopping the airplane from its present position, the automatic processor conditionally issuing a warning to the pilot to abort takeoff if the remaining distance on the runway is adequate to stop the airplane and the actual airplane speed is below V.'}2. The system of wherein said automatic processor computes airplane actual instantaneous weight in response to the sensors.3. The system of wherein the automatic processor computes minimum acceptable rotation speed.4. The system of wherein the automatic processor computes distances required to attain rotation claim 1 , lift-off and 35 foot-height above the runway claim 1 , considering an all-engine-operating condition.5. The system of wherein the automatic processor evaluates the energy absorbed by the airplane brakes in case of an aborted takeoff.6. The system of wherein the automatic processor evaluates the climb gradient available at lift-off claim 1 , considering an all-engine-operating condition.7. The system of wherein the automatic processor warns the pilot to abort takeoff if a large deviation is detected between the airplane weight as determined by the automatic processor and one inputted by the pilot.8. The system of wherein the automatic processor warns the pilot to abort takeoff if rotation speed proposed by the pilot is lower than the minimum acceptable for actual airplane operating conditions.9. The system of wherein ...

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22-08-2013 дата публикации

AIRCRAFT WITH FUSELAGE-MOUNTED ENGINES AND AN INTERNAL SHIELD

Номер: US20130214090A1
Принадлежит: AIRBUS OPERATIONS S.L.

Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material; the internal shield being located in said vertical symmetry plane and extended in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of said engines in a failure event that would impact on critical elements of the opposite engine; the internal shield having a flat shape and an energy absorption capability that allows stopping said fragments. The invention also refers to a method for determining the area of an internal shield and to an aircraft having said internal shield. 1. Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material , characterized in that:the internal shield is located in said vertical symmetry plane and extended in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of said engines in a failure event that would impact on critical elements of the opposite engine;the internal shield has a flat shape and an energy absorption capability that allows stopping said fragments.2. Internal shield according to claim 1 , wherein its energy absorption capability is comprised between 5-100 kJ.3. Internal shield according to claim 1 , which is made of a rigid material or of a deformable material or of a combination of several layers of rigid and/or deformable materials.4. Internal shield according to claim 3 , wherein said rigid material is one of the following: titanium claim 3 , high performance steel claim 3 , aluminum claim 3 , carbon fiber reinforced material claim 3 , glass fiber reinforced material claim 3 , kevlar fiber reinforced material ...

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22-08-2013 дата публикации

Method and System For Highlighting a Flight Path Deviation of an Aircraft

Номер: US20130218373A1
Принадлежит:

A method and system for highlighting a flight path deviation of an aircraft to a user in a multi-parameter aircraft instrument display, such as a flat panel display. A visibility attribute is configured to toggle between a standard state when the actual aircraft position is within a predetermined range of the target aircraft position, and an enhanced state when the actual aircraft position is outside the predetermined range. The electronic display is configured to highlight a flight path deviation when in the enhanced state, such as by displaying deviation scales having an actual aircraft position indicator relative to the target position, and increasing the size or changing the color of certain displayed elements, or displaying/concealing new elements. Such display features aid in focusing the pilot's attention to deviations from optimal flight paths and ensuring navigation accuracy and, therefore, safety. 1. An apparatus for indicating flight path deviation for an aircraft , the apparatus comprising:a graphics rendering controller configured to generate an instrumentation image; and a deviation scale comprising an actual aircraft position indicator representative of an actual aircraft position;', 'a pointer movable along the deviation scale to represent the target aircraft position; and', a standard state when the actual aircraft position is within a predetermined range of the target aircraft position; and', 'an enhanced state when the actual aircraft position is outside the predetermined range of the target aircraft position;, 'a visibility attribute configured to toggle between], 'the instrumentation image comprises, 'an electronic display coupled to the graphics rendering controller to present the instrumentation image;'}wherein the electronic display is configured to highlight a flight path deviation when in the enhanced state.2. The apparatus of claim 1 , wherein:the instrumentation image further comprises an attitude indicator image; andthe deviation scale ...

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29-08-2013 дата публикации

DEVICE AND METHOD FOR EXCHANGING INFORMATION BETWEEN AT LEAST ONE OPERATOR AND A MACHINE

Номер: US20130222347A1
Принадлежит: AIRBUS OPERATIONS GMBH

A device and a method for exchanging information between at least one operator and a machine which comprises the following components: a display means, which is set up so as to display information from the machine to the at least one operator visually and three-dimensionally; an input means, which is set up so as to detect the position of objects, preferably the position of the fingers of at least one operator, in three-dimensional space in relation to the display means, in a time-resolved manner by optical and/or acoustic and/or electromagnetic measurement methods, and to detect at least one operator input from the detected progression over time in accordance with at least one predetermined criterion and to pass said operator input on to the machine. 1. A device for exchanging information between at least one operator and a machine which comprises the following components:a display means, which is set up so as to display information from the machine to the at least one operator visually and three-dimensionally;an input means, which is set up so as to detect the position of objects, preferably the position of the fingers of at least one operator, in three-dimensional space in relation to the display means, in a time-resolved manner by optical and/or acoustic and/or electromagnetic measurement methods, and to detect at least one operator input from the detected progression over time in accordance with at least one predetermined criterion and to pass said operator input on to the machine.2. The device according to claim 1 , wherein the display means is an autostereoscopic glasses-free 3D display.3. The device according to claim 1 , wherein at least one aircraft cabin system is controlled and monitored by way of the exchange of information.4. The device according to claim 3 , wherein the image produced by the display means has a basic layout in which the individual system menus claim 3 , which are each associated with at least one aircraft cabin system claim 3 , are ...

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29-08-2013 дата публикации

SYSTEM FOR DETECTING THE FIRST SIGNS OF A MALFUNCTION OF AN AIRCRAFT ENGINE VALVE

Номер: US20130226395A1
Принадлежит: SNECMA

A method and a system for detecting the first signs of malfunction of an aircraft engine valve, including an acquisition device to acquire the output pressure measurements of the valve, and contextual and command data of the valve, a processor to define a set of indicators of the first signs of malfunction, according to the output pressure measurements and the contextual and command data. A set of estimators corresponding to the set of indicators of the first signs of a malfunction, is determined using a previously produced regression model. At least one distance between the set of indicators and the set of estimators is computed. The distance is compared to a threshold of the first signs of a malfunction, in order to detect the first signs of malfunction of the said valve. 1. A system for detecting the first signs of a malfunction of an aircraft engine valve , comprising:an acquisition device to acquire the output pressure measurements of said valve, and contextual and command data of said valve,a processor configured to define a set of indicators of the first signs of malfunction, according to said output pressure measurements and said contextual and command data, wherein said processor is further configured to determine a set of estimators corresponding to said set of indicators of the first signs of a malfunction, using a previously produced regression model,said processor being further configured to compute at least one distance between said set of indicators and said set of estimators, andsaid processor being further configured to compare said at least one distance to at least one threshold of the first signs of a malfunction, in order to detect the first signs of malfunction of the said valve.2. A system according to claim 1 , wherein the contextual data includes data of ambient pressure claim 1 , of valve feed pressure and of temperature measurements claim 1 , and wherein the command data includes instants when the orders are given to open and close said ...

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05-09-2013 дата публикации

DEVICE FOR DISPLAY AND CONTROL OF SETPOINTS FOR AUTOMATIC PILOTING FOR AIRCRAFT

Номер: US20130231804A1
Принадлежит: THALES

The general field of the invention is that of devices for display and control of setpoints for automatic piloting for aircraft, configured to display the setpoints of speed, heading, climb slope and altitude. The various setpoints are displayed in the form of a graphical representation comprising: wheels graduated in speed and in altitude indicating the aircraft setpoint values; a circular heading rose, graduated and centred on a first symbol representing the aircraft, the heading setpoint being indicated by a second symbol representing the heading to be followed by the aircraft and disposed around the perimeter of the heading rose; and a vertical sectional view comprising a graduated semicircle centred on a third symbol representing the aircraft, the slope setpoint being indicated by a fourth symbol representing the slope to be followed by the aircraft and disposed around the perimeter of the semicircle. 1. Device for display and control of setpoints for automatic piloting for aircraft , the said device comprising a viewing screen configured to display at least the setpoints of speed , heading , climb slope and altitude of the aircraft , characterized in that the various setpoints are displayed in the form of a graphical representation comprising:a first wheel graduated in speed and a second wheel graduated in speed, the first wheel indicating the setpoint speed of the aircraft in a coarse manner, the second wheel indicating the setpoint speed of the aircraft in a precise manner, the precision of the second wheel being about a decade greater than the precision of the first wheel;a circular heading rose, graduated and centred on a first symbol representing the aircraft, the heading setpoint being indicated by a second symbol representing the heading to be followed by the aircraft and disposed around the perimeter of the heading rose;a third wheel graduated in climb speed indicating the setpoint climb speed of the aircraft;a vertical sectional view comprising a ...

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19-09-2013 дата публикации

SITUATIONAL AWARENESS PILOT BRIEFING TOOL

Номер: US20130245860A1
Автор: Cooper Jennifer
Принадлежит: GE AVIATION SYSTEMS LIMITED

Embodiments of the present invention relate to a system and method for better conveying information to a pilot and/or other members of a flight crew present on the flight deck of an aircraft. Embodiments of the invention are of particular use in the briefings that precede various phases of the flight operations of an aircraft (such as start-up of the engines, take-off, ascent to cruise altitude, descent from cruise altitude and landing). The system and method provide a briefing output relevant to the particular phases of a flight in both of a visual form and an audio form, with the briefing output including data of most relevance to the particular flight phase. 1. A situational awareness briefing system for a flight crew of an aircraft , wherein the system is operable to interrogate data from a plurality of sources , wherein the system comprises:a selection filter for filtering the interrogated data to provide a selected subset of the interrogated data relevant to at least one part of a flight of the aircraft;a multisensory output device for providing a briefing output based upon the selected subset of the interrogated data, the briefing output comprising at least two of actions required of the flight crew relevant to the at least one part of the flight; settings of aircraft on-board systems relevant to the at least one part of the flight; and information provided by at least one information source off-board the aircraft relevant to the at least one part of the flight; a visual form to provide a visual simulation, confirmation or representation of the actions, settings or information, and', 'an audio form to provide an auditory simulation, confirmation or representation of the actions, settings or information., 'wherein the multisensory output device is operable to provide at least a part of the briefing output in both'}2. A situational awareness briefing system according to claim 1 , wherein the system is operable to request an acknowledgement input signal from the ...

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26-09-2013 дата публикации

AIRCRAFT SPEED GUIDANCE DISPLAY

Номер: US20130253738A1
Автор: Fucke Lars
Принадлежит:

The invention relates to systems and methods for displaying flight information representative of a deviation from a specified four-dimensional flight path. Particularly, but not exclusively, the invention relates to a cockpit display for enabling pilots to arrive at a particular location at a particular time and to achieve the necessary changes to aircraft speed to achieve a preferred ground speed. 1. A method of displaying flight information relating to a predetermined flight path that specifies locations and scheduled times corresponding thereto , the method comprising the steps of:monitoring a current location of an aircraft along the predetermined flight path;determining a current time at which the aircraft is at the current location;providing a scheduled time for the aircraft to be at the current location;calculating a time deviation between the current time and the scheduled time; anddisplaying the time deviation.2. The method of claim 1 , further comprising the step of providing a desired ground speed for the aircraft at the current location.3. The method in accordance with claim 2 , wherein the desired ground speed is a scheduled ground speed.4. The method in accordance with claim 2 , further comprising the steps of:monitoring a current ground speed of the aircraft;calculating a ground speed deviation between the current ground speed and the desired ground speed; anddisplaying the ground speed deviation.5. The method in accordance with claim 2 , further comprising the step of displaying the desired ground speed.6. The method in accordance with claim 5 , further comprising the steps of:monitoring the aircraft's current ground speed data, current airspeed data, current heading data, and current track data;defining a maximum operating airspeed for the aircraft;calculating a maximum permissible ground speed deviation based upon the defined maximum operating airspeed, the current airspeed data, the current ground speed data, the current heading data, and the ...

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17-10-2013 дата публикации

FLIGHT DATA MONITORING AND VALIDATION

Номер: US20130274964A1
Принадлежит: FLIGHT DATA SERVICES LIMITED

A computer-implemented flight data monitoring method is provided for monitoring flight data, for example flight data obtained by a flight data recorder or quick access recorder on an aircraft. The method comprises receiving input flight data, performing flight data validation on the input flight data to generate validated flight data, and performing flight data analysis on the validated flight data to detect at least one predetermined type of flight event. The events may be useful for generating an aircraft safety report, for example. By validating the data before performing the analysis, the number of events which are falsely detected based on invalid or unreliable data can be reduced. 1. A computer-implemented flight data monitoring method comprising:receiving input flight data;performing flight data validation on the input flight data to generate validated flight data; andperforming flight data analysis on the validated flight data to detect at least one predetermined type of flight event.2. The flight data monitoring method according to claim 1 , wherein the input flight data comprises a set of parameters sampled at time intervals providing a series of data values for each parameter.3. The flight data monitoring method according to claim 2 , wherein a data value or parameter which fails the flight data validation is identified as invalid.4. The flight data monitoring method according to claim 3 , wherein the flight data analysis excludes data values or a parameter identified as invalid by the flight data validation.5. The flight data monitoring method according to claim 2 , wherein the flight data validation comprises at least one of:(a) a repeating pattern test for detecting occurrences of a repeating signal pattern in data values of a parameter of the input flight data;(b) a spike detection test for detecting spikes in the data values of a parameter of the input flight data;(c) a range comparison test for determining whether data values of a parameter of the ...

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17-10-2013 дата публикации

Method And System For Detecting Pushrod Faults

Номер: US20130274989A1
Принадлежит:

A system for monitoring for pushrod faults in an aircraft includes a pushrod; a sensor () mounted on the pushrod (), the sensor () wirelessly transmitting measured pushrod load data; a receiver () receiving the measured pushrod load data; a model () receiving flight data and generating a modeled pushrod load profile; and a fault detector () comparing measured pushrod load data to the modeled pushrod load profile to detect a pushrod fault. 1. A system for monitoring for pushrod faults in an aircraft , the system comprising:{'b': '34', 'a pushrod ();'}{'b': 36', '34, 'a sensor () mounted on the pushrod (), the sensor wirelessly transmitting measured pushrod load data;'}{'b': '44', 'a receiver () receiving the measured pushrod load data;'}{'b': '42', 'a model () receiving flight data and generating a modeled pushrod load profile; and'}{'b': '46', 'a fault detector () comparing the measured pushrod load data to the modeled pushrod load profile to detect a pushrod fault.'}2. The system of wherein:comparing the measured pushrod load data to the modeled pushrod load profile includes determining a difference between the measured pushrod load data and the modeled pushrod load profile.3. The system of wherein:comparing the measured pushrod load data to the modeled pushrod load profile includes determining if the measured pushrod load data is similar to a pushrod fault signature generated by the model.4. The system of wherein:comparing the measured pushrod load data to the modeled pushrod load profile includes comparing harmonics of the measured pushrod load data to harmonics of the modeled pushrod load profile.5. The system of wherein:{'sup': st', 'nd', 'th, 'the harmonics include the 1, 2and/or nharmonics, for an n-bladed rotor system.'}6. The system of further comprising:{'b': '48', 'a results file () storing a result of the comparing the measured pushrod load data to the modeled pushrod load profile.'}7. The system of further comprising:{'b': 50', '60, 'a transmitter () ...

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24-10-2013 дата публикации

METHOD AND DEVICE FOR CONFIGURING AN ALERTS MANAGEMENT SYSTEM FOR AN AIRCRAFT

Номер: US20130282206A1
Принадлежит: THALES

A method and a device for configuring an alerts management system for an aircraft comprises: generating a list of a plurality of alerts and of resolution procedures for an aircraft; for each alert, defining: distinctive characteristics of the alert; logic for detecting the alert; at least one procedure for resolving the alert; and, for each alert, defining recording in a dedicated alerts file the set of information defined for said alert, the alerts file having a structure and a format of data that are predefined for the alerts and the procedures; determining existing links between the dedicated alerts files; and in response to the determining step, updating the content of the dedicated alerts files according to the links identified. 1. A method executed on a computer for configuring an alerts management system for an aircraft , comprising the steps of:generating a list comprising a plurality of alerts and of resolution procedures for an aircraft; [ distinctive characteristics of the alert;', 'logic for detecting the alert;', 'at least one procedure for resolving the alert; and, 'defining, 'recording in a dedicated alerts file the set of information defined for said alert, the alerts file having a structure and a format of data that are predefined for the alerts and the procedures;, 'for each alertdetermining existing links between the dedicated alerts files; andin response to the determining step, updating the content of the dedicated alerts files according to the links identified.2. The method as claimed in claim 1 , in which the step of defining the distinctive characteristics of the alert consists in defining an alert message claim 1 , an attention means claim 1 , a priority level or alert disablers.3. The method as claimed in claim 1 , in which the step of defining logic for detecting the alert consists in defining logic based on boolean operators and mathematical operators.4. The method as claimed in claim 1 , in which the step of defining at least one ...

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14-11-2013 дата публикации

APPARATUS FOR UNMANNED VEHICLE

Номер: US20130304282A1
Принадлежит: BAE SYSTEMS plc

An apparatus and a method are disclosed, such as an apparatus wholly or partially mounted on an unmanned vehicle and arranged to act upon a payload, the payload being mounted on the unmanned vehicle and, under an action of the apparatus, being changeable from being in a first state to being in a second state. The method can include: receiving an instruction that the unmanned vehicle, with the payload mounted thereon, is to travel to a location; determining that the payload is in the first state; and responsive to determining that the payload is in the first state: opposing the payload being changed to being in the second state; and providing, for an entity remote from the unmanned vehicle, an indication that the payload is in the first state. 1. A method performed by an apparatus , the apparatus being wholly or partially mounted on an unmanned vehicle and arranged to act upon a payload , the payload being mounted on the unmanned vehicle and , under an action of the apparatus , being changeable from a first state to being in a second state , the method comprising:receiving an instruction that the unmanned vehicle, with the payload mounted thereon, is to travel to a location;determining that the payload is in the first state; and opposing the payload being changed to being in the second state; and', 'providing, for an entity remote from the unmanned vehicle, an indication that the payload is in the first state., 'responsive to the step of determining that the payload is in the first state2. A method according to claim 1 , wherein operation of the payload in the first state is restricted compared to operation of the payload in the second state.3. A method according to claim 1 , wherein the step of opposing the payload being changed to being in the second state comprises:disabling a mechanism by which the payload is changed to being in the second state.4. A method according to claim 1 , wherein the step of opposing the payload being changed to being in the second state ...

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14-11-2013 дата публикации

Parametrizable system for centralized maintenance intended for an aircraft

Номер: US20130304420A1
Принадлежит: Thales SA

A system for centralized maintenance, intended for an aircraft comprising a set of devices necessary for the flight and able to issue fault messages or alert messages, the maintenance system being able to communicate with this set of devices, comprises a software kernel parametrizable by means of a database of parameters, the software kernel comprising at least four elementary cells: a first cell for acquiring the fault messages and alert messages originating from the set of devices of the aircraft, a second cell for formulating a maintenance diagnosis defined by means of the fault messages and alert messages, a third cell for formulating and displaying a maintenance report to a maintenance operator of the aircraft, defined on the basis of the maintenance diagnosis, a fourth cell for communicating between the maintenance operator and the set of devices of the aircraft.

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21-11-2013 дата публикации

AIRCRAFT AND METHOD FOR DISPLAYING A VISUAL INFORMATION ASSOCIATED TO FLIGHT PARAMETERS TO AN OPERATOR OF AN AIRCRAFT

Номер: US20130307705A1
Автор: Wang James
Принадлежит: AGUSTAWESTLAND S.p.A.

There is described an aircraft, comprising a windscreen arranged in a front side of aircraft, characterized in that an edge of windscreen defines a visualization area visible by an operator, and by comprising displaying means configured for displaying at least one visual information of at least one flight parameter within visualization area, at least when aircraft is in a normal flight configuration. 11111) An aircraft ( , ′ , ″ , ′″) , comprising:{'b': 2', '5, 'a fuselage () with a nose ();'}{'b': 4', '2', '5, 'a tail rotor () fitted to a tail fin projecting from said fuselage () at the opposite end of said nose ();'}{'b': 6', '7, 'a cockpit () housing an instrument console (); and'}{'b': 50', '50', '50', '50', '1', '1', '1', '1, 'a windscreen (, ′, ″, ′″) arranged in a front side of said aircraft (, ′, ″, ′″);'}{'b': 50', '50', '50', '50', '55', '59, 'said windscreen (, ′, ″, ′″) comprising an edge () which confines a visualization area () visible by an operator;'}{'b': 1', '1', '1', '1', '58', '20', '25, 'said aircraft (, ′, ″, ′″) further comprising displaying means () capable to display at least one visual information (, ) associated to at least one flight parameter{'b': '6', 'at least in part inside said cockpit (); and/or'}{'b': '6', 'at least in part outside said cockpit (); and/or'}{'b': 50', '50', '50', '50, 'at least in part on said windscreen (, ′, ″, ′″);'}{'b': 20', '25', '59', '1', '1', '1', '1, 'said visual information (, ) being visible by said operator inside said visualization area (), at least when said aircraft (, ′, ″, ′″) is in a normal flight configuration;'}{'b': 20', '25', '25', '1', '1', '1', '1, 'said visual information (, ) comprising at least one first image () associated at least to the orientation of said aircraft (, ′, ″, ′″) relative to the earth;'}{'b': 25', '26, 'characterized in that said first image () comprises at least one line () parallel, in use, to the line of horizon;'}{'b': 26', '7', '1', '1', '1', '1', '5', '4, 'said ...

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28-11-2013 дата публикации

ELECTRONIC AVIONICS SYSTEMS AND METHODS

Номер: US20130314258A1
Принадлежит: ASPEN AVIONICS, INC.

The present general inventive concept relates to a system of method having an electronic flight display that meets the FAR 23.1311(b) regulatory requirement for redundant backup instruments in the cockpit. The present general inventive concept also provides a system and method to detect failures, obstructions, or improper operation of the aircraft pitot pressure sensing system using a combination of dissimilar sensor data that is independent from each other, e.g., allocated from different sources and employed for different purposes on different displays, and displays information on an avionics display screen. 1. An electronic avionics system comprising:a first avionics display operably connected with a first air data computer and a first attitude computer;a second avionics display operably connected with a second air data computer and a second attitude computer; anda communications connection linking said first and second avionics displays;wherein information is transmitted between said first and second avionics displays via said communications connection; andwherein hardware functions of said first avionics display and said second avionics display operate independent of one another.2. The electronic avionics system of claim 1 , wherein said first avionics display is integrated with said first air data computer and said first attitude computer.3. The electronic avionics system of claim 1 , wherein said first air data computer and said first attitude computer is a single processor.4. The electronic avionics system of claim 1 , wherein said first air data computer claim 1 , said first attitude computer and a computer of said first display are sub-routines performed by a single processor.5. The electronic avionics system of claim 1 , wherein said information comprises essential information regarding pilot settings or unit health.6. The electronic avionics system of claim 1 , wherein each of said first and said second display is connected to a power source independent ...

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28-11-2013 дата публикации

METHOD AND SYSTEM OF TRANSMITTING AND RECEIVING DATA ORIGINATING FROM AN AIRCRAFT BLACK BOX

Номер: US20130317673A1
Принадлежит:

The invention relates to a method for transmitting data, characterized in that it includes a step of transmitting in-flight data between a first aircraft and at least a second aircraft, the data transmitted being data stored in at least one black box on board the first aircraft. 1. A data transmission method , comprising a step of transmitting data in flight between a first aircraft and at least a second aircraft , the data transmitted being data stored in at least one black box on board the first aircraft.2. A method according to claim 1 , wherein the data originating from the at least one black box requires for its transmission a bandwidth of at least 100 kbits/s.3. A method according to claim 1 , comprising a prior step of selecting a communication means from a plurality of communication means.4. A method according to claim 3 , wherein the means of communication comprise radio claim 3 , satellite or any other wireless communication.5. A method according to one of claim 1 , wherein the data is transmitted on a communication network comprising mobile communication nodes that are aircraft in flight.6. A method according to claim 5 , comprising claim 5 , prior to the transmission step claim 5 , a step of selecting in flight at least one non-predetermined mobile communication node claim 5 , the at least one node being selected from a set of mobile communication nodes in the network as a function of at least one predetermined selection criterion.7. A method according to claim 6 , wherein the at least one predetermined selection criterion is at least one of the following criteria: an aircraft producing a signal-to-noise ratio above a predetermined threshold claim 6 , an aircraft having a similar or identical flight plan(s) claim 6 , an aircraft belonging to the same airline or the same alliance of several airlines claim 6 , an aircraft made by the same manufacturer claim 6 , an aircraft within communication range claim 6 , the aircraft furthest away from the first ...

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05-12-2013 дата публикации

METHOD AND DEVICE FOR AUTOMATICALLY ESTIMATING A DEGRADATION IN FUEL CONSUMPTION AND IN DRAG OF AN AIRCRAFT

Номер: US20130325219A1
Принадлежит:

A method and device for automatically estimating a degradation in fuel consumption and in drag of an aircraft. The device comprises a device for calculating a numerical value of the effect of a degradation in performance on the fuel consumption and/or the drag of the aircraft, and an arrangement for displaying this numerical value on a screen in the cockpit of the aircraft. 1. A method for estimating a degradation in performance of an aircraft , according to which method , at a step a) , an acquisition is carried out in real time of data comprising at least air and inertial data and satellite positioning data , wherein , on the aircraft during a flight , in addition to step a) , the following sequence of steps is carried out in an automatic and repetitive manner:b) a re-adjustment of the air and inertial data is carried out with the aid of said satellite positioning data;c) at least one numerical value is calculated of the effect of a degradation in performance on at least one of the following parameters of the aircraft: the fuel consumption and the drag, by comparing the current state of this parameter, which is calculated starting from said re-adjusted air and inertial data with the aid of at least one performance model, with a theoretical state of said parameter; andd) this numerical value thus calculated of the effect of a degradation in performance on said parameter is displayed on at least one screen in the cockpit of the aircraft.2. The method as claimed in claim 1 ,wherein at step b), the re-adjustment is carried out by calculating a bias of the air and inertial data representing a total slope bias and by correcting with the aid of this bias the air and inertial data which are used at step c).3. The method as claimed in claim 1 ,wherein at an intermediate step between steps c) and d), it is verified, according to the attitude parameters of the aircraft, whether the numerical value calculated at step c) is valid or not, and if it is not valid, it is fixed at ...

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12-12-2013 дата публикации

Attitude and Configuration Indicator Display System and Method

Номер: US20130328702A1
Принадлежит:

Attitude and Configuration Indicator Display System and Method within the context of an Electronic Instrument System in which the configuration status of a piloted craft; typically the instant positions of lift inducing elements and drag inducing elements, are represented by symbol groupings integrated with an a parent icon, typically a chevron-type symbol representative of the piloted craft. The symbol groupings receive data from associated on-board sensors and are displayed singly or in combination with each other anytime the piloted craft is not in a clean configuration to instantly alert the pilot(s) of the configuration status with a single glance directed to the attitude indicator. 1. An electronic Attitude and Configuration Indicator display system comprising:(1) an attitude indicator display,(2) a two-dimensional parent icon with a border residing within bounds of the attitude indicator display in which the parent icon represents a piloted craft, and wherein position of the parent icon indicates at least the pitch and the roll of the piloted craft, and,(3) a plurality of child symbol groups adjacent to or on the border of the parent icon wherein each group represents a category of elements associated with the configuration of the piloted craft and moves in concert with the parent icon and remains fully visible within the same plane as any other child symbol group when displayed, regardless of the indicated pitch and roll.2. The Attitude and Configuration Indicator display according to in which each child symbol group is displayed or hidden in response to real time data from sensors on the piloted craft.3. The attitude and Configuration Indicator display system according to wherein each child symbol group is distinguishable from any other child symbol group by at least its characteristics of position and shape relative to the parent icon.4. The Attitude and Configuration Indicator display according to in which the plurality of child symbol groups have at ...

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26-12-2013 дата публикации

AIRCRAFT HOVER SYSTEM AND METHOD

Номер: US20130345909A1
Автор: Block Gerald J.
Принадлежит: SANDEL AVIONICS, INC.

An aircraft hover system for enabling an aircraft to hover at a target spatial location represented by GPS location coordinates. The hover system includes a display screen rendering a display including live video feed of the terrain below the airborne aircraft, a first mark overlaying the video feed, the first mark representing the current position of the aircraft relative to the terrain, and a perimeter surrounding the first mark, the portion of the terrain within the perimeter being substantially magnified compared to that of the terrain outside of the perimeter. The hover system is configured such that, as the aircraft approaches the target spatial location, the distance between the first mark and a second mark on the display gradually decreases until and finally the first and second marks coincide; the second mark representing the target spatial location. 2. The hover system of claim 1 , wherein the display further comprises an altitude indicator section displaying a current pointer representing the current altitude of the aircraft claim 1 , and a target pointer representing a target altitude of the aircraft; and such that the distance between the current and target pointers is configured to decrease as the aircraft arrives at the target altitude from the current altitude.3. The hover system of claim 1 , further comprising means for delivering an aural alert as the aircraft nears the target spatial location.4. The hover system of claim 3 , wherein the aural alert further includes a success alert claim 3 , the success alert being delivered when the first and second marks are coincident to within a predetermined tolerance.5. The hover system of claim 3 , wherein the aural alert further includes a stray alert claim 3 , which is delivered when the aircraft claim 3 , upon arriving at the target spatial location claim 3 , strays therefrom claim 3 , by an amount greater than a threshold.6. The hover system of claim 1 , wherein at any point claim 1 , the visibility of ...

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02-01-2014 дата публикации

CONFIGURATION AND MONITORING SYSTEM FOR AN AIRCRAFT CABIN ELEMENT, FUSELAGE AND AIRCRAFT COMPRISING SAID SYSTEM AND METHOD OF MONITORING AN AIRCRAFT

Номер: US20140002278A1
Принадлежит: INTERTECHNIQUE

The invention relates to a method and a configuration and monitoring system for an aircraft cabin element of a plurality of cabin elements in a cabin of an aircraft, the system comprising: 1. A configuration and monitoring system for an aircraft cabin element of a plurality of cabin elements in a cabin of an aircraft , the system comprising:a radio frequency identification (RFID) device, wherein the RFID-device is associated with the aircraft cabin element adapted for providing a monitor signal adapted to indicate a status of the aircraft cabin element by a monitor information,a RFID-reader communicatingly connectable to the RFID-device,a controlling unit of a central cabin system, characterized in thatthe RFID-reader is communicatingly integrated in the central cabin system by being continuously communicatingly connectable to the controlling unit in the cabin, wherein information are centrally collectable and accessable by the controlling unit, andat least one repeater is adapted for expanding the monitor signal in the cabin to the RFID-reader, wherein the monitor information includes continuously, responding status data of the aircraft cabin element during the flight.2. A configuration and monitoring system according to claim 1 , wherein the aircraft cabin element including the continuously claim 1 , responding status data is adapted to a cabin component and/or a cabin supply item.3. A configuration and monitoring system according to claim 1 , wherein a RFID-device and a sensor unit is assigned to the RFID-device and/or the RFID-reader claim 1 , in particular a sensor unit integrated in the RFID-device and/or the RFID-reader claim 1 , communicating continuously claim 1 , responding status data providing analyzable and transponder callable status data.4. A configuration and monitoring system according to claim 1 , wherein the continuously claim 1 , responding status data of the RFID-device provides health and usage data.5. A configuration and monitoring system ...

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02-01-2014 дата публикации

CABIN SERVICE ARRANGEMENT, FUSELAGE OF AN AIRCRAFT, A METHOD OF EFFECTING A CABIN ATTENDANT CALL

Номер: US20140002279A1
Принадлежит: INTERTECHNIQUE

This invention relates to cabin service arrangement assigned to at least one passenger seat in a seat row of an aircraft, comprising: 1. A cabin service arrangement assigned to at least one passenger seat in a seat row of an aircraft , comprising:a lighting unit for providing a light projection and at least one man machine interface for operating the lighting unit, wherein an initiating unit for providing an activation of the lighting unit and', 'a deactivation unit for receiving an indication for deactivation of the light projection, wherein the deactivation is initialisable by an external signal, and wherein, 'the at least one man machine interface is associated with'}the light projection from the lighting unit comprises an illumination, the illumination being adapted to effect a cabin attendant call,characterized in thatthe illumination is adapted to be projected to a projection spot outside of the seat row, andthe deactivation of the illumination is effectable from outside of the seat row.2. A cabin service arrangement according to wherein the illumination is projectable outside of the seat row's occupation area and the deactivation of the illumination is effectable outside of the seat row's occupation area.3. A cabin service arrangement according to wherein at least one of the initiating unit and deactivation unit has a sensor unit adapted to receive a touch free user input to the man machine interface.4. A cabin service arrangement according to wherein the illumination provides stored information of the passenger seat to the projection spot outside of the seat row claim 1 , in particular wherein the illumination comprises one or more lighting effects selected from the group consisting of: a light sign claim 1 , a highlighter claim 1 , a light pattern claim 1 , in particular claim 1 , flashing claim 1 , varying in color claim 1 , intensity and/or place of spot as a function of time.5. A cabin service arrangement according to wherein a control unit is adapted to ...

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30-01-2014 дата публикации

Mechanical position indicator

Номер: US20140026808A1
Принадлежит: Messier Dowty Ltd

A mechanical position indicator for providing a visual indication that a first part of an aircraft landing gear has assumed a predetermined position relative to a second part, the position indicator being arranged to be coupled to a first one of the first and second parts and in a first state arranged to hold an indicator element in a deployed position, the position indicator being arranged such that upon the first part assuming the predetermined position relative to the second part, a second one of the first and second parts changes the position indicator from the first state to a second state in which the indicator element is displaced from the deployed position, the position indicator being arranged to inhibit the indicator element thereafter returning to the deployed position.

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06-02-2014 дата публикации

METHOD AND APPARATUS FOR PROVIDING IN-FLIGHT WEATHER DATA

Номер: US20140039733A1
Принадлежит: GENERAL ELECTRIC COMPANY

A method for providing one or more aircraft with weather data during flight includes generating a weather model using a source of weather data. The weather model incorporates flight operations information and performance requirements. The method includes generating a weather message from the weather model. The weather message is generated in a format that is compatible with the aircraft. The method also includes transmitting the weather message to the aircraft during flight of the aircraft. 1. A method for providing one or more aircraft with weather data during flight , the method comprising:generating a weather model using a source of weather data, wherein the weather model incorporates flight operations information and performance requirements;generating a weather message from the weather model, the weather message being generated in a format that is compatible with the aircraft; andtransmitting the weather message to the aircraft during flight of the aircraft.2. The method of claim 1 , further comprising transmitting the weather message to at least one of an air traffic control (ATC) entity or an aircraft operator entity that controls operation of one or more of the aircraft.3. The method of claim 1 , wherein generating a weather model using a source of weather data comprises:integrating the flight operations information and the performance requirements to determine weather performance requirements;receiving weather data from the source of weather data; andgenerating the weather model according to the weather data and the weather performance requirements.4. The method of claim 3 , wherein integrating the flight operations information and the performance requirements to determine weather performance requirements comprises:consolidating the flight operations information of the aircraft with flight operations information of an air traffic control (ATC) entity; andconsolidating the performance requirements of the aircraft with performance requirement of the ATC ...

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20-02-2014 дата публикации

METHOD OF PROVIDING A FIRE-RESISTANT LAMINATE HAVING A PRINT ADVERTISEMENT FOR A CABIN COMPONENT OF AN AIRCRAFT

Номер: US20140050901A1
Автор: Adams Kirk R.
Принадлежит: Global Onboard Partners, LLC

An advertisement laminate meets the fire-resisting requirements needed for placement inside of an aircraft cabin. The laminate includes several specifically configured adhesively attached layers, including a fire protection barrier layer, a printed advertisement layer which is visible to passengers, and a transparent protective cover layer. The laminate is equipped for being adhesively adhered to an interior component of the aircraft cabin, such as an overhead storage bin, an overhead bin door, a sidewall panel, a bulkhead, window surround, or any other area inside the aircraft which must meet FAR 25.853 requirements. 1. A method of manufacturing a fire-resisting laminate structure configured for connection to an interior component of an aircraft , comprising: wherein the vinyl film layer has a thickness of approximately 2.0 mils+/−10%,', 'wherein the vinyl film layer includes at least one graphic marking disposed directly on a side thereof;, '(a) providing a first laminate component including a vinyl film layer,'} 'wherein the PVF film layer has a thickness of approximately 1.0 mil+/−10%;', '(b) providing a second laminate component including a fire-resisting transparent polyvinyl fluoride (PVF) film layer,'} wherein the first adhesive material comprises a pressure-sensitive clear acrylic adhesive,', 'wherein the first adhesive material has a thickness in the range of approximately 0.9-1.0 mil+/−0.1,', 'wherein the at least one graphic marking is visible through the second laminate component;, '(c) using a first adhesive material to directly adhere the second laminate component to the first laminate component,'} [ wherein the fabric includes continuous filament fiberglass woven from glass yarn,', {'sup': '2', 'wherein the fabric has a weight in the range of approximately 13.5-15.0 oz/yd+/−10%,'}], 'wherein the fire protection layer includes a fabric,'}, 'wherein the fire protection layer includes at least one brominated compound,', 'wherein the fire protection ...

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27-02-2014 дата публикации

Cable Cutting Device for Aircraft

Номер: US20140054414A1
Принадлежит:

The invention disclosed relates to a cable-cutting device for cutting a cable under tension. The device is intended for use in conjunction with aircraft, particularly helicopters, to provide reasonable protection from cable strikes. The device includes a main body carrying in a bottom recess a pair of co-acting cable-cutting edges arranged at a suitable angle to produce a wedge-like mechanical advantage to at least partially cut a cable so that the cable will fail under moderate tension. The main body is formed of a composite material defined by a light weight foam central core and wrappings of carbon fiber fabric infused by a resin where the blades are molded into the walls of the recess. 1. Apparatus arranged for mounting on an aircraft for cutting a cable under tension when impacted by the aircraft during flight comprising:a main body for mounting on the aircraft at a suitable location adjacent to the front nose of the aircraft;the main body having a base for attachment to a suitable structural component of the aircraft;the main body being shaped to define an arm extending outwardly and forwardly from the base to a tip at a position spaced outwardly from the base;the main body having a leading front surface extending from the tip toward the base for guiding movement of the cable toward the base as the aircraft moves forwardly;the main body having a trailing rear surface extending from the tip toward the base behind the front edge and a pair of side surfaces interconnecting the front and rear surfaces to form a solid body cantilevered from the base;the main body defining a recess in the front surface adjacent the base into which recess the cable can enter as it slides along the front edge;a first blade carried on the main body in the recess at a position outward of the base with a cutting edge of the first blade facing the base;a second blade carried on the main body in the recess on a side of the recess inward of the first blade with a cutting edge of the second ...

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13-03-2014 дата публикации

Aircraft avionics tablet interface module

Номер: US20140074322A1
Принадлежит: Rosemount Aerospace Inc

An aircraft avionics system including an aircraft interface device configured to communicate with an aircraft avionics system and a tablet interface module configured to communicate with the aircraft interface device and with one or more tablets. The aircraft avionics system includes a plurality of sensors for an aircraft and the tablet interface module provides the one or more tablets with information received from the aircraft interface device.

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13-03-2014 дата публикации

METHOD OF DETERMINING A TURBULENT CONDITION IN AN AIRCRAFT

Номер: US20140074326A1
Автор: Pereira Frazer Leslie
Принадлежит: GE AVIATION SYSTEMS LLC

A method of determining a turbulent condition in an aircraft with a handheld device where the handheld device has at least one of a gyroscope, seismometer, and an accelerometer where the method includes receiving an output from the at least one of the gyroscope, seismometer, and accelerometer while the handheld device is located within the aircraft and providing an indication of a turbulent condition. 1. A method of determining a turbulent condition in an aircraft with a handheld device having at least one of a gyroscope , seismometer , and an accelerometer , the method comprising:receiving an output from the at least one of the gyroscope, seismometer, and accelerometer while the handheld device is located within the aircraft;comparing the received output to a turbulence threshold value for the received output; andproviding an indication of a turbulent condition when the comparison indicates the received output exceeds the turbulence threshold value.2. The method of wherein the receiving the output comprises receiving an angle output from the gyroscope indicative of at least one of a pitch claim 1 , roll and yaw angle of the aircraft.3. The method of claim 2 , further comprising determining a rate of change for at least one of the pitch claim 2 , roll and yaw angle from the angle output.4. The method of wherein the comparing comprises comparing the rate of change to a corresponding rate of change threshold value.5. The method of wherein the receiving the output comprises receiving a motion output from the seismometer.6. The method of wherein the motion output is indicative of vibration motion of the aircraft.7. The method of wherein the receiving the output comprises receiving acceleration output from the accelerometer.8. The method of wherein the acceleration output is indicative of the acceleration in multi-dimensional motion of the aircraft.9. The method of wherein the receiving the output comprises:receiving an angle output from the gyroscope indicative of a ...

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10-04-2014 дата публикации

INFRARED LIGHT ENABLED AND ELECTROMAGNETIC SHIELDING AIRCRAFT WINDOW

Номер: US20140097017A1
Автор: Russell Shawn P.
Принадлежит: The Boeing Company

A flight deck aircraft window has improved transparency from two layers of different types of glass and electromagnetic radiation shielding from a thin layer of indium tin oxide between the two layers of glass. The thin layer of indium tin oxide provides the required shielding without appreciably adding to the window weight or detracting from the enhanced transparency of the two layers of glass. 1. An aircraft window comprising:a first glass layer extending across the aircraft window, the first glass layer being water white glass; and,a second glass layer extending across the aircraft window, the second glass layer overlapping the first glass layer, the second glass layer being a glass that is different from water white glass.2. The aircraft window of claim 1 , further comprising:a layer of adhesive between the first glass layer and the second glass layer, the layer of adhesive contacting both the first glass layer and the second glass layer and securing together the first glass layer and the second glass layer.3. The aircraft window of claim 1 , further comprising:the aircraft window having an outboard side that faces an exterior of an aircraft on which the aircraft window is installed, and an opposite inboard side that faces an interior of the aircraft on which the aircraft window is installed;the first glass layer is proximate the outboard side of the aircraft window and the second glass layer is proximate the inboard side of the aircraft window.4. The aircraft window of claim 1 , further comprising:a layer of electromagnetic shielding material extending across the aircraft window between the first and second glass layers.5. The aircraft window of claim 4 , further comprising:the layer of electromagnetic shielding material is on the second glass layer.6. The aircraft window of claim 4 , further comprising:the layer of electromagnetic shielding material is indium tin oxide.7. The aircraft window of claim 4 , further comprising:the aircraft window having a ...

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10-04-2014 дата публикации

INCLINATION DETECTION DEVICE FOR AIRCRAFT, AND METHOD FOR LOADING AND UNLOADING CARGO USING SAME

Номер: US20140097297A1
Автор: Yanagawa Hiroki
Принадлежит: MITSUBISHI AIRCRAFT CORPORATION

An inclination detection device for an aircraft includes a gravity sensor that detects an inclination angle in a pitch direction at a parking time of a fuselage an alarm device and a control unit that causes the device to issue an alarm when the inclination angle detected by the sensor approaches allowable limit inclination angles F and R in a forward inclination direction and a backward inclination direction of the fuselage The control unit has gravity center management information peculiar to the fuselage inputted therein by a USB memory or the like, and corrects a movable range in the forward and—backward inclination directions until the inclination angle reaches the angles F and R based on the gravity center management inclination information, before a loading and unloading operation of cargo into and from the fuselage 1. An inclination detection device for an aircraft , comprising:an inclination angle detection means that detects an inclination angle in a pitch direction at a parking time of a fuselage;an alarm; anda control means that causes the alarm to issue an alarm when the inclination angle detected by the inclination angle detection means approaches allowable limit inclination angles in a forward inclination direction and a backward inclination direction of the fuselage.2. The inclination detection device for an aircraft according to claim 1 ,wherein the control means has gravity center management information peculiar to the fuselage inputted therein, and corrects a movable range in the forward inclination direction and the backward inclination direction until the inclination angle reaches the limit inclination angles based on the gravity center management information, before a loading and unloading operation of cargo into and from the fuselage.3. The inclination detection device for an aircraft according to claim 1 ,wherein the inclination detection device can be installed in an arbitrary place of the fuselage.4. The inclination detection device for an ...

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10-04-2014 дата публикации

Method and device for displaying flight parameters on an aircraft

Номер: US20140100722A1
Принадлежит:

The display device comprises display means which highlight on a screen, preferably of PFD type, the information useful to the pilot relating to at least one flight parameter, especially while reducing the corresponding scale on said screen. 1. A method of displaying flight parameters on an aircraft , with the aid of at least one viewing screen comprising display elements dedicated to given flight parameters which each comprise at least one corresponding scale , said aircraft being capable of being guided by a guidance system according to one of a plurality of guidance modes , according to which method said aircraft guidance system is monitored so as to be able to detect a situation in which: the aircraft is guided by said guidance system according to a guidance mode having as an objective at least one given guidance setpoint relating to a given flight parameter and said guidance mode holds this given guidance setpoint , and wherein , when such a situation is detected , a scale part which is reduced to a size corresponding at most to a holding range for said guidance setpoint is highlighted on the display element dedicated to said flight parameter and displayed on the viewing screen , wherein a check is performed to verify whether the motion of the aircraft is consistent with a guidance setpoint relating to a flight parameter , and wherein:if the motion of the aircraft is consistent with this guidance setpoint, then displaying only a part of the scale onward of the current value of this flight parameter, doing so in the direction of the motion of the aircraft; andif the motion of the aircraft is not consistent with a guidance setpoint, unraveling the scale in a first and a second, opposite direction with respect to the current value of the flight parameter.2. The method as claimed in claim 1 , wherein claim 1 , if it is detected that said aircraft is guided with the holding of a plurality of guidance setpoints claim 1 , highlighting a reduced scale part for each of ...

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01-01-2015 дата публикации

SYSTEM AND METHOD FOR TIRE BURST DETECTION

Номер: US20150002318A1
Автор: Cahill Eric
Принадлежит:

Tire pressure monitoring systems and methods for detecting a tire burst are disclosed. The system may include a tire pressure sensor, a tire pressure monitor, and a tire burst indicator. The tire pressure sensor may measure tire pressure in an aircraft tire. The tire pressure monitor may analyze data from the tire pressure sensor to detect a tire burst. A tire burst may be detected in response to a rapid decrease in tire pressure. In response to detecting a tire burst, the tire pressure monitor may transmit a tire burst message to the tire burst indicator. The tire burst indicator may indicate to a pilot that a tire burst has been detected. 1. A system for detecting a tire burst comprising:a tire pressure sensor;a tire pressure monitor for registering the tire burst in response to a decrease in tire pressure measured by the tire pressure sensor; anda tire burst indicator which indicates the tire burst in response to the tire pressure monitor registering the tire burst.2. The system of claim 1 , wherein the tire burst indicator indicates which tire has burst.3. The system of claim 1 , wherein the tire pressure monitor registers the tire burst in response to the tire pressure decreasing by greater than 50% within 50 milliseconds.4. The system of claim 1 , wherein the tire pressure monitor registers the tire burst in response to detecting a rate of decrease of the tire pressure of at least 1 claim 1 ,000 psi per second.5. The system of claim 1 , wherein the tire burst indicator is a binary indicator.6. The system of claim 1 , wherein the tire pressure monitor identifies a tire pressure leak.7. The system of claim 1 , wherein the tire pressure sensor is coupled to an aircraft tire.8. A method comprising:measuring a tire pressure with a tire pressure sensor;determining, by a processor and in response to a decrease in the tire pressure, that a tire burst has occurred; andindicating, with a tire burst indicator, that the tire burst has occurred.9. The method of claim 8 , ...

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07-01-2016 дата публикации

AFT PYLON FAIRING FOR AIRCRAFT

Номер: US20160001888A1
Принадлежит:

Aft fairings for aircraft pylons are disclosed. In one example, a fairing includes: two opposite side panels extending generally along a longitudinal direction of the fairing; a plurality of transverse ribs interconnecting the two opposite side panels; and a heat shield for exposure to a primary flow of an aircraft engine. The heat shield includes transversely opposed side end portions and a mid portion disposed between the transversely opposed side end portions. The heat shield is secured to the ribs via the mid portion of the heat shield. The transversely opposed side end portions are permitted to move outwardly from the mid portion due to thermal expansion of the heat shield. 1. An aft fairing of a pylon where the pylon is suitable for securing an engine to structure of an aircraft , the fairing comprising:two opposite side panels extending generally along a longitudinal direction of the fairing;a plurality of transverse ribs interconnecting the two opposite side panels, the ribs being spaced apart from each other along the longitudinal direction; anda heat shield for exposure to a primary flow of the engine, the heat shield extending generally along the longitudinal direction, the heat shield comprising transversely opposed side end portions and a mid portion disposed between the transversely opposed side end portions, the heat shield being secured to the ribs via the mid portion of the heat shield, the transversely opposed side end portions being permitted to move outwardly from the mid portion due to thermal expansion of the heat shield.2. The aft fairing as defined in claim 1 , comprising a non-rigid connection between the transversely opposed side end portions of the heat shield and respective ones of the side panels.3. The aft fairing as defined in claim 2 , wherein the non-rigid connection is configured to guide movement of the transversely opposed side end portions of the heat shield relative to the respective side panels.4. The aft fairing as defined in ...

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02-01-2020 дата публикации

PASSENGER COMMUNICATION SYSTEM

Номер: US20200002023A1
Принадлежит: Safran Seats USA LLC

A communication system for a vehicle seat includes a visual indicator having a lighting mechanism configured to display a plurality of colors, a control portion electrically connected to the visual indicator, and a plurality of modes. Each mode may be associated with one of the plurality of Selection of one of the plurality of modes causes the control portion to signal the lighting mechanism to display the color associated with the selected mode. 1. A communication system for a vehicle seat , the communication system comprising:a visual indicator comprising a lighting mechanism configured to display a plurality of colors;a control portion electrically connected to the visual indicator; anda plurality of modes, wherein:each mode is associated with one of the plurality of colors; andselection of one of the plurality of modes causes the control portion to signal the lighting mechanism to display the color associated with the selected mode.2. The communication system of claim 1 , wherein the visual indicator displays a distinct visual indicia for each mode and the visual indicator comprises an LED light.3. The communication system of claim 1 , wherein the plurality of modes comprises a Do Not Disturb mode wherein the visual indicator illuminates as a solid red light.4. The communication system of claim 1 , wherein the plurality of modes comprises a Wake Me for Meals/Beverage mode wherein the visual indicator illuminates as a solid blue light.5. The communication system of claim 1 , wherein the plurality of modes comprises at least three of a Do Not Disturb mode claim 1 , a Wake Me for Meals/Beverage mode claim 1 , a Need Assistance mode claim 1 , a Wake Me for Duty-Free mode claim 1 , a Medical Emergency mode claim 1 , and a Vacant Seat mode.6. The communication system of claim 1 , wherein the visual indicator is disposed on an upper surface of a seatback.7. The communication system of claim 6 , wherein the visual indicator further comprises an auxiliary light disposed ...

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03-01-2019 дата публикации

DEVICE FOR MONITORING A TURBINE ENGINE OF AN AIRCRAFT

Номер: US20190003396A1
Принадлежит:

An aircraft including at least one turbine engine and a monitoring device associated with the turbine engine, the turbine engine being linked firstly to circuits including fluid circuits and electric circuits, and secondly to sensors for monitoring the turbine engine and the circuits, the sensors including at least one fire sensor and sensors for monitoring the fluid circuits, sensors for monitoring the electric circuits and sensors for monitoring the operation of the turbine engine, the monitoring device being linked to the sensors and including a central processing unit to generate a signal indicating the occurrence of a fire on the turbine engine only if a fire sensor and a sensor for monitoring a fluid circuit or an electric circuit or the operation of the turbine engine transmit a signal indicating an anomaly. 1. An aircraft comprising at least one turbine engine and a monitoring device associated with the turbine engine , the turbine engine being linked firstly to a plurality of circuits including fluid circuits and electric circuits , and secondly to a plurality of sensors for monitoring the turbine engine and the plurality of circuits , the plurality of sensors comprising at least one fire sensor and sensors for monitoring the fluid circuits , sensors for monitoring the electric circuits and sensors for monitoring operation of the turbine engine , wherein the monitoring device is linked to the plurality of sensors and comprises a central processing unit to generate a signal indicating an occurrence of a fire on the turbine engine only if a fire sensor and a sensor for monitoring a fluid circuit or an electric circuit or the operation of the turbine engine transmit a signal indicating an anomaly.2. The aircraft according to claim 1 , the aircraft comprising a plurality of fire sensors claim 1 , wherein each fire sensor is associated with at least one sensor for monitoring a fluid circuit or an electric circuit or the operation of the turbine engine claim 1 , ...

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03-01-2019 дата публикации

DISENGAGEABLE DAMPING ASSEMBLIES FOR MOVING AERODYNAMIC SURFACES

Номер: US20190003551A1
Автор: BLOCH Serge, Grand Serge
Принадлежит:

A damping assembly is described herein for use in a device having moving aerodynamic surfaces including a first component comprising a back iron and at least one permanent magnet, said at least one permanent magnet providing a first magnetic field, and an electrically conductive second component, said electrically conductive second component and said first component being positioned coaxially about a central axis with said at least one permanent magnet being positioned between said back iron of said first component and said electrically conductive second component; the assembly further comprising means for rotating one or both of said at least one permanent magnet of said first component and said electrically conductive second component about said central axis to cause relative rotational movement between the at least one permanent magnet and second component, to thereby induce a variable magnetic flux in said electrically conductive second component and cause eddy currents to develop. 1. A disengagable damping assembly for use in a device having moving aerodynamic surfaces comprising:a first component comprising a back iron and at least one permanent magnet, said at least one permanent magnet providing a first magnetic field, and;an electrically conductive second component,said electrically conductive second component and said first component being positioned coaxially about a central axis with said at least one permanent magnet being positioned between said back iron of said first component and said electrically conductive second component;the assembly further comprising:means for rotating one or both of said at least one permanent magnet of said first component and said electrically conductive second component about said central axis to cause relative rotational movement between the at least one permanent magnet and second component, to thereby induce a variable magnetic flux in said electrically conductive second component and cause eddy currents to develop ...

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01-01-2015 дата публикации

METHOD FOR DETECTING A FAILURE OF AT LEAST ONE SENSOR ONBOARD AN AIRCRAFT IMPLEMENTING WIND DETECTION, AND ASSOCIATED SYSTEM

Номер: US20150006021A1
Принадлежит:

A method for detecting a failure of at least one sensor onboard an aircraft implementing wind detection is provided. The method includes measuring an airspeed of the aircraft; measuring a geographical speed of the aircraft; determining an instantaneous wind vector, based on the measured airspeed and geographical speed; establishing an instantaneous wind variation vector, based on the determined instantaneous wind vector; projecting the instantaneous wind variation vector on the direction of the vector of an air or geographical speed of the aircraft; and determining the presence of a failure based on the obtained projection. 1. A method for detecting a failure of at least one sensor onboard an aircraft , including the following steps:measuring an airspeed of the aircraft;measuring a geographical speed of the aircraft;determining an instantaneous wind vector based on the measured airspeed and geographical speed;establishing an instantaneous wind variation vector based on the determined instantaneous wind vector;projecting the instantaneous wind variation vector on the direction of the vector of an air or geographical speed of the aircraft to obtain an instantaneous wind variation vector projection;determining the presence of a failure based on the instantaneous wind variation vector projection.2. The method as recited in wherein the determining the presence of a failure includes comparing the instantaneous wind variation vector projection with a given threshold.3. The method as recited in wherein the value of the given threshold varies as a function of the flight phase.4. The method as recited in further comprising filtering the instantaneous wind variation vector projection claim 1 , before the determining the presence of a failure claim 1 , using an angular band pass filter centered on the direction of the air or geographical speed.5. The method as recited in wherein the filtering the instantaneous wind variation vector projection includes normalizing the ...

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04-01-2018 дата публикации

Cooling system for cooling electronic aircraft equipment, aircraft equipped with a cooling system for cooling electronic aircraft equipment and method for cooling electronic aircraft equipment

Номер: US20180007813A1
Принадлежит:

A cooling system for cooling electronic aircraft equipment comprises a primary cooling arrangement configured to provide basic cooling energy for cooling the electronic aircraft equipment and a supplemental cooling arrangement configured to provide supplemental cooling energy for cooling the electronic aircraft equipment. The supplemental cooling arrangement comprises a coolant supply system and a coolant distribution system. The coolant supply system is configured to supply a compressed coolant to the electronic aircraft equipment to be cooled, and the coolant distribution system is configured to selectively direct the compressed coolant supplied by the coolant supply system to at least one of a plurality of components of the electronic aircraft equipment. 1. A cooling system for cooling electronic aircraft equipment , comprising:a primary cooling arrangement configured to provide basic cooling energy for cooling the electronic aircraft equipment; and a coolant supply system configured to supply a compressed coolant to the electronic aircraft equipment to be cooled; and', 'a coolant distribution system configured to selectively direct the compressed coolant supplied by the coolant supply system to at least one of a plurality of components of the electronic aircraft equipment., 'a supplemental cooling arrangement configured to provide supplemental cooling energy for cooling the electronic aircraft equipment, wherein the supplemental cooling arrangement comprises2. The cooling system of claim 1 , wherein the compressed coolant supplied by the coolant supply system comprises an inert gas.3. The cooling system of claim 1 , wherein the coolant supply system comprises:a coolant source for providing the coolant to be supplied to the electronic aircraft equipment; anda coolant supply control device connected to the coolant source and configured to control a supply of compressed coolant from the coolant source to the coolant distribution system.4. The cooling system of ...

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12-01-2017 дата публикации

AIRCRAFT TURBULENCE DETECTION

Номер: US20170008639A1
Принадлежит: Safe Flight instrument Corporation

A warning method for an aircraft includes receiving a first parameter indicative of an aircraft's flight path, calculating a stable approach value based on the first parameter, receiving a second parameter indicative of the aircraft's turbulence, calculating a turbulence factor based on the second parameter, calculating a safe landing value based on the stable approach value and the turbulence factor, comparing the safe landing value to a threshold value, and providing an aircraft warning when the safe landing value fails to meet the threshold value. 1. A warning method for an aircraft comprising:receiving a first parameter indicative of an aircraft's flight path,calculating a stable approach value based on the first parameter,receiving a second parameter indicative of the aircraft's turbulence,calculating a turbulence factor based on the second parameter,calculating a safe landing value based on the stable approach value and the turbulence factor,comparing the safe landing value to a threshold value, andproviding an aircraft warning when the safe landing value fails to meet the threshold value.2. The method of claim 1 , wherein the first parameter comprises the aircraft's vertical speed and the aircraft's height above the ground.3. The method of claim 1 , wherein the second parameter comprises the aircraft's pitch rate and the aircraft's vertical acceleration rate.4. The method of claim 3 , wherein the aircraft's pitch rate comprises a frequency of a pitch's oscillation.5. The method of claim 3 , wherein the aircraft's vertical acceleration rate comprises a maximum vertical acceleration over a period of time.6. The method of claim 1 , wherein the second parameter comprises a frequency of a vertical acceleration rate of the aircraft.7. The method of claim 1 , wherein the second parameter comprises an acceleration of the aircraft about an axis claim 1 , a rate of change of an acceleration of the aircraft about an axis claim 1 , a yaw rate of the aircraft claim 1 , or ...

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12-01-2017 дата публикации

FLIGHT MANAGEMENT ASSEMBLY FOR AN AIRCRAFT AND METHOD FOR MONITORING SUCH AN ASSEMBLY

Номер: US20170008640A1
Автор: MERE Jean-Claude
Принадлежит:

A flight management assembly for an aircraft and method for monitoring such an assembly. The flight management assembly includes two guidance systems each provided with a flight management system, the flight management systems being independent, each of the flight management systems carrying out at least one calculation of roll commands for the aircraft, the flight management assembly also comprising a data generating unit, preferably forming part of a guidance computer, for calculating a roll command and a monitoring unit for carrying out a monitoring of the roll commands calculated by the two flight management systems and by the data generating unit in such a way as to be able to detect and identify a defective flight management system. 1. A flight management assembly for an aircraft , the flight management assembly comprising two guidance systems , each of the guidance systems comprising a flight management system , each flight management system being independent and hosted in different equipment , each flight management system being configured for carrying out , in real time , at least a calculation of guidance commands for the aircraft , the guidance commands comprising at least a roll command , the flight management assembly also comprising at least one monitoring unit configured for carrying out monitorings of data generated by the flight management systems to be able to detect an inconsistency ,the flight management assembly comprising at least one data generating unit, different from the flight management systems, the data generating unit being configured for calculating, in real time, a roll command,the monitoring unit being configured for, at least in case of detection of an inconsistency in the data of the flight management systems, carrying out a comparison of the roll commands calculated by the two flight management systems with the roll command determined by the data generating unit to be able to detect and identify, if applicable, a defective flight ...

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09-01-2020 дата публикации

AIRCRAFT EQUIPPED WITH A SYSTEM FOR ESTIMATING THE PARAMETERS OF AN IMPACT

Номер: US20200010166A1
Принадлежит:

An aircraft with a system for estimating the parameters of an impact. The aircraft includes a skin forming an outer surface of the aircraft, the aircraft equipped with a system for estimating the parameters of an impact including an array of sensors attached to the skin and a central processing unit connected to the array, the array of sensors including a first set of sensors providing data relating to elastic waves, the central processing unit configured for assessing the parameters of an impact from the data of the sensor array and a response model of the skin to external excitations calculated from the modal properties of the skin. 1. An aircraft comprising a skin forming an outer surface of the aircraft , the aircraft comprising a system for estimating parameters of an impact comprising an array of sensors attached to the skin and a central processing unit connected to the array of sensors , the array of sensors comprising a first set of sensors providing data relating to elastic waves , the central processing unit configured for assessing the parameters of an impact from the data of the array of sensors and a response model of the skin to external excitations calculated from modal properties of the skin.2. The aircraft according to claim 1 , wherein the sensors of the first set of sensors are located at neutral points of the skin of the aircraft relative to discriminant vibration eigenmodes of the skin.3. The aircraft according to claim 1 , wherein the sensors of the first set of sensors are accelerometers.4. The aircraft according to claim 1 , wherein the array of sensors comprises a second set of sensors providing data relating to temporal detection of an impact instant.5. The aircraft according to claim 4 , wherein the sensors of the second set of sensors are located in areas of the aircraft statistically most affected by impacts.6. The aircraft according to claim 4 , wherein the sensors of the second set of sensors are microphone sensors or piezoelectric ...

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12-01-2017 дата публикации

SYSTEM AND METHOD FOR IMPROVED DRIVE SYSTEM DIAGNOSTICS

Номер: US20170011560A1
Принадлежит: SIKORSKY AIRCRAFT CORPORATION

A method of drive system diagnostics of an aircraft includes capturing high load drivetrain component vibration data at select steady-state and/or high-load transient operating conditions of the aircraft and processing the captured vibration data to improve reliability and/or accuracy of captured vibration data. The processed vibration data is utilized to provide a health assessment of the drivetrain components and achieve earlier detection of incipient faults. A health monitoring system for drivetrain components of an aircraft includes a plurality of vibration sensors positioned at drivetrain components of an aircraft to capture drivetrain component vibration data at transient operating conditions of the aircraft. One or more processing modules process the captured vibration data to improve reliability and/or accuracy of the captured data, and a fault reasoning module calculates a health indicator of the drivetrain components. 1. A method of drive system diagnostics of an aircraft comprising:capturing high load drivetrain component vibration data at select steady-state and/or high-load transient operating conditions of the aircraft;processing the captured vibration data to improve reliability and/or accuracy of the captured vibration data; andutilizing the processed vibration data to provide a health assessment of the drivetrain components and achieve earlier detection of incipient faults.2. The method of claim 1 , further comprising:sensing load at one or more drivetrain components; andtriggering the capture of drivetrain component vibration data when the sensed load indicates a selected operating mode for data capture.3. The method of or claim 1 , further comprising:monitoring parametric data of the aircraft operation;utilizing a virtual monitoring of loads module to estimate an aircraft load based on the parametric data;triggering the capture of drivetrain component vibration data when the estimated load indicates a selected operating mode for data capture.4. ...

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14-01-2021 дата публикации

AIRCRAFT ACTUATOR FLUID LEVEL DETECTION

Номер: US20210010844A1
Автор: Ankney Darrell E.
Принадлежит:

Disclosed is an actuator level detection system of an aircraft. The system includes an actuator containing fluid that defines a resistivity and including a first contact point and a second contact point. The system includes a first contactor disposed about the actuator cooperating with the first contact point to define a first contact resistance that includes the resistivity. The system includes sensor circuitry includes a conductive path defining a conductive path resistance, between the first contact point and the second contact point. The sensor circuitry has a total resistance that includes the first contact resistance and the conductive path resistance. 1. An actuator level detection system of an aircraft , the system comprising:an actuator containing fluid that defines a resistivity and including a first contact point and a second contact point;a first contactor disposed about the actuator cooperating with the first contact point to define a first contact resistance that includes the resistivity; andsensor circuitry including a conductive path defining a conductive path resistance, between the first contact point and the second contact point, the sensor circuitry having a total resistance that includes the first contact resistance and the conductive path resistance.2. The actuator level detection system of claim 1 , further comprising a controller having stored instructions operable upon execution to quantify the total resistance.3. The actuator level detection system of claim 2 , wherein the stored instructions are further operable upon execution to indicate actuator fluid loss based on the total resistance falling outside a loss threshold.4. The actuator level detection system of claim 2 , wherein the stored instructions are further operable upon execution to indicate contaminated fluid based on the total resistance falling outside a contamination threshold.5. The actuator level detection system of claim 1 , wherein the sensor circuitry is part of ...

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03-02-2022 дата публикации

DUAL-FILTER-BASED TRANSFER ALIGNMENT METHOD UNDER DYNAMIC DEFORMATION

Номер: US20220033100A1
Принадлежит:

A dual-filter-based transfer alignment method under dynamic deformation. A dynamic deformation angle generated under dynamic deformation and a coupling angle between dynamic deformation and body motion will reduce the accuracy of transfer alignment; and a transfer alignment filter is divided into two parts, the first part estimates a bending deformation angle and the coupling angle, and uses an attitude matching method, and the second part estimates a dynamic lever arm, and uses a “speed plus angular speed” matching method. 1. A dual-filter-based transfer alignment method under dynamic deformation , applied to an aircraft wing deformation measurement system , in which a main inertial navigation system is installed in a cabin and inertial navigation subsystems are installed on the wings , wherein the method comprises the following steps:generating attitude, speed and position information of the main inertial navigation system and outputs of a gyro and an accelerometer by using a trajectory generator, simulating flexural deformation angle {right arrow over (θ)} and flexural deformation angular speed {dot over ({right arrow over (θ)})} between the main inertial navigation system and the inertial navigation subsystems by using a second-order Markov, carrying out geometric analysis on the flexural deformation, and deriving an expression of coupling angle Δ{right arrow over (ϕ)} resulted from dynamic deformation of the carrier and movement of the carrier;{'b': '1', 'using the flexural deformation angle, the flexural deformation angular speed and the coupling angle as state quantities, and establishing a model of filter with an attitude matching method;'}establishing a dynamic lever arm model by using the flexural deformation angle and the coupling angle estimated in step (2), and deriving an expression of speed error and an expression of angular speed error;{'b': '2', 'establishing a model of filter by using the expression of speed error and expression of angular speed ...

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19-01-2017 дата публикации

SYSTEM AND METHOD FOR DETECTING AND ALERTING THE USER OF AN AIRCRAFT OF AN IMPENDENT ADVERSE CONDITION

Номер: US20170015434A1
Автор: MCKAY David Edward
Принадлежит:

A method detects an impendent situation of an operating aircraft. The method comprises receiving data corresponding to a plurality of parameters related to an operation of the aircraft. It is determined if any of the plurality of parameters is at or beyond at least a first respective threshold by comparing the plurality of parameters with the first respective thresholds. If at least one of the parameters is an outlier parameter at or beyond its first respective threshold, another or others of the plurality of parameters associated to the at least one outlier parameter is identified, the at least one other parameter being selected based on a predetermined combination of parameters representative of an adverse condition. The associated parameters are compared with a stored data combination threshold specific to the associated parameters. A signal indicative of an impending situation is output if the associated parameters are on or beyond the data combination threshold. A system and an aircraft detecting an impendent situation are also provided. 1. A method for detecting an impendent situation of an operating aircraft , the method comprising:receiving data corresponding to a plurality of parameters related to an operation of the aircraft;determining if any of the plurality of parameters is at or beyond at least a first respective threshold by comparing the plurality of parameters with the first respective thresholds; identifying at least one other of the plurality of parameters associated to the at least one outlier parameter, the at least one other parameter being selected based on a predetermined combination of parameters representative of an adverse condition,', 'comparing the associated parameters with a stored data combination threshold specific to the associated parameters, and', 'outputting a signal indicative of an impending situation if the associated parameters are on or beyond the data combination threshold., 'if at least one of the parameters is an outlier ...

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19-01-2017 дата публикации

CALIBRATION OF TRANSDUCERS

Номер: US20170016792A1
Автор: HEALEY Mark, SHEPHERD Alan
Принадлежит:

A load measuring sensor set on an aircraft is used under the control of a control unit on the aircraft. The load measuring sensor set is calibrated and there is calibration data associated with it. A code is retrieved which identifies uniquely the sensor set, so that a remote database can be interrogated using the code to retrieve the correct calibration data for the sensor set, for use by the control unit. The sensor set may utilise an optical-fibre having a Fibre Bragg Grating arrangement which provides optical signature characteristics that provide the unique code and having a Fibre Bragg Grating arrangement configured to measure loads. 1. A method of setting up a load measuring sensor on an aircraft , whereinthe loads are to be measured using a calibrated sensor set under the control of a control unit which uses calibration data associated with the calibrated sensor set,the sensor set and the control unit are both located on the aircraft, andwherein the method includes the following steps:retrieving a code that identifies uniquely the calibrated sensor set located on the aircraft;interrogating a remote database using the code to retrieve calibration data that is associated with the calibrated sensor set located on the aircraft; andtransmitting the retrieved calibration data to the control unit.2. A method according to claim 1 , wherein the method includes a step of calibrating the sensor set to produce the calibration data that is associated with the calibrated sensor set.3. A method according to claim 1 , wherein the method includes a step of providing a unique code and physically associating the code with the calibrated sensor set.4. A method according to claim 1 , wherein the step of retrieving a code includes retrieving electronically the code from the sensor set or something that is physically associated with the sensor set.5. A method according to claim 1 , wherein the method includes the steps of:calibrating the sensor set to produce the calibration data ...

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17-01-2019 дата публикации

FLIGHT DECK TIMER MANAGEMENT SYSTEMS AND METHODS

Номер: US20190016472A1
Принадлежит: HONEYWELL INTERNATIONAL INC.

A flight deck timer management system includes a database storing conditions representing a first monitoring mode defining at least a first rule, a first timing characteristic defining a first time period for compliance with the first rule, and a first advisory value relative to the first time period at which a first advisory is initiated. A control unit is configured to identify input states based on the input data, and to evaluate the input states in view of the first monitoring mode conditions. When the input states trigger the first monitoring mode, the control unit evaluates the input states in view of the first rule, initiates a first timer based on the first timing characteristic, monitors a first timing status of the first timer relative to the first advisory value, and generates display commands representing the first advisory when the first timer status reaches the first advisory value. 1. A flight deck timer management system , comprising:a database storing conditions representing a first monitoring mode defining at least a first rule, a first timing characteristic defining a first time period for compliance with the first rule, and a first advisory value relative to the first time period at which a first advisory is initiated;a control unit coupled to the database and configured to receive input data, to identify input states based on the input data, and to evaluate the input states in view of the first monitoring mode conditions, evaluate the input states in view of the first rule,', 'initiate a first timer based on the first timing characteristic,', 'monitor a first timing status of the first timer relative to the first advisory value, and', 'generate display commands representing the first advisory when the first timer status reaches the first advisory value; and, 'wherein, when the input states trigger the first monitoring mode, the control unit is configured to'}a display device coupled to the control unit and configured to display the first ...

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15-01-2015 дата публикации

DISPLAY SYSTEMS AND METHODS FOR PROVIDING DISPLAYS HAVING AN ADAPTIVE COMBINED VISION SYSTEM

Номер: US20150019048A1
Принадлежит:

A method for providing a display to a flight crew of an aircraft includes the steps of providing a synthetic image comprising a first field of view forward of a direction of travel of the aircraft and providing a sensory image overlaying at least a first portion of the synthetic image. The sensory image includes a second field of view forward of the direction of travel of the aircraft. At least a portion of the first field of view and a portion of the second field of view overlap one another. The sensory image is centered within the synthetic image with respect to a horizontal axis. The method further includes moving the sensory image so as to overlay at least a second portion of the synthetic image such that the sensory image is no longer centered with respect to the horizontal axis within the synthetic image. 1. A method for providing a display to a flight crew of an aircraft comprising the steps of:providing a synthetic image comprising a first field of view forward of a direction of travel of the aircraft;providing a sensory image overlaying a first portion of the synthetic image, the sensory image comprising a second field of view forward of the direction of travel of the aircraft, wherein at least a portion of the first field of view and the second field of view overlap one another, and wherein the sensory image is centered within the synthetic image with respect to a horizontal axis; andmoving the sensory image so as to comprise a third field of view forward of the direction of travel of the aircraft and so as to overlay a second portion of the synthetic image such that the sensory image is no longer centered with respect to the horizontal axis within the synthetic image, wherein at least a portion of the first field of view and the third field of view overlap one another.2. The method of claim 1 , wherein the second field of view and the third field of view at least partially overlap one another.3. The method of claim 1 , further comprising providing a ...

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18-01-2018 дата публикации

SYSTEM AND METHOD FOR DYNAMICALLY DETERMINING AND INDICATING AN AIRCRAFT BANK LIMIT ON AN AIRCRAFT INSTRUMENT PANEL

Номер: US20180017410A1
Принадлежит:

Systems and methods are provided for indicating a bank limit on an instrument display of an aircraft. In an example implementation, static air pressure measurements, impact air pressure measurements, an acceleration measurement, and an angle of attack may be received from corresponding sensors. A current airspeed and a stick shaker speed are determined. A minimum maneuver speed is determined from the current airspeed and the shaker stick speed. A bank limit indicator is provided on the flight display when the current airspeed is equal to or less than the minimum maneuver speed. A bank angle limit is displayed on the bank limit indicator based on the extent to which the current airspeed is equal to or less than the minimum maneuver speed. 1. A method for indicating a bank limit on an instrument display in an aircraft comprising:receiving a static air pressure measurement from a static air pressure sensor;receiving an impact air pressure measurement from a pitot air pressure sensor;receiving an acceleration measurement from an accelerometer;receiving an angle of attack measurement from an angle of attack sensor;determining a current airspeed based on the impact air pressure measurement and the static air pressure measurement;determining a stick shaker speed based on the current airspeed;determining a minimum maneuver speed based on the current airspeed, the acceleration measurement and the stick shaker speed;displaying a bank limit indicator on a flight display when the current airspeed is equal to or less than the minimum maneuver speed; anddisplaying a bank angle limit on the bank limit indicator based on an extent to which the current airspeed is equal to or less than the minimum maneuver speed.2. The method of where the step of displaying the bank angle limit further includes:determining the bank angle limit for display on the bank limit indicator to a maximum bank angle limit when the current airspeed is equal to the minimum maneuver speed, to a minimum bank ...

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21-01-2021 дата публикации

Non-Volatile Multiple Time Programmable Integrated Circuit System with Selective Conversion to One Time Programmable or Permanent Configuration Bit Programming Capabilities and Related Methods

Номер: US20210016885A1
Автор: Armes Craig Michael

The present invention relates to a turreted electro-optic sensor installation and removal fixture. the base with integral cushion supports the sensor vertically and is the interface between the turreted electro-optic sensor installation and removal fixture and an agnostic lift device. The support arms with integral cushions secure the sensor horizontally and minimize any swaying movement of the sensor. The quick disconnect pins lock the support arms to the base. 1. A turreted fixture comprising:a base comprising a plurality of clips and a base cushion, wherein the base is formed with a plurality of base retention apertures;a plurality of support arms, wherein each support arm comprises a pad, wherein each support arm is formed with an arm retention aperture;a plurality of pins;wherein each support arm is adapted to engage with the base by sliding horizontally into the base such that each pad is disposed above an upper surface of the base and below two clips of the plurality of clips;wherein each pin is adapted to pass through a corresponding base retention aperture and arm retention aperture to hold a corresponding support arm of the plurality of support arms in place.2. The fixture of claim 1 , wherein each pin further comprises a lanyard claim 1 , wherein each lanyard is coupled to the base.3. The fixture of claim 1 , further comprising:a sensor, wherein the base cushion is coupled to the sensor with friction, wherein the plurality of support arms are adapted to hold the sensor when the plurality of support arms are engaged with the base.4. The fixture of claim 1 , wherein each support arm is coupled to a device such that the turreted fixture hangs below the device.5. The fixture of claim 4 , wherein the device is an aircraft.6. The fixture of claim 3 , wherein the sensor is coupled to a device such that the turreted fixture hangs below the device.7. The fixture of claim 6 , wherein the device is an aircraft. This application claims priority to U.S. Provisional ...

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17-04-2014 дата публикации

Aircraft cockpit with head-up display device

Номер: US20140104693A1
Автор: MANJON SANCHEZ Javier
Принадлежит:

An aircraft cockpit comprises a head-up display device comprising a projector and a screen, the screen being placed facing a pilot along a theoretical line of sight of the pilot. The projector is fixed to a side wall of the cockpit, the screen forming a non-zero angle of inclination relative to a plane perpendicular to the theoretical line of sight of the pilot. 1. An aircraft cockpit comprising a head-up display device comprising at least one projector and a screen , said screen being placed facing a pilot along a theoretical line of sight of the pilot , wherein said at least one projector is fixed to a side wall of the cockpit , located on the side of the pilot when said pilot is looking in the theoretical line of sight of the pilot , said screen forming a non-zero angle of inclination relative to a plane perpendicular to said theoretical line of sight of the pilot.2. The aircraft cockpit according to claim 1 , where in the head-up display device comprises two projectors respectively fixed to two opposite side walls of the cockpit.3. The aircraft cockpit according to claim 2 , wherein said screen is rotatable on a screen bracket claim 2 , between a first position in which the projection center of the screen is located in the projection axis of a first of said projectors and a second position in which the projection center of the screen is located in the projection axis of the second of said projectors.4. The aircraft cockpit according to claim 3 , wherein the head-up display device comprises means of rotating the screen claim 3 , the rotation means being controlled by a control signal sent by a control system depending on the operating status of said two projectors.5. The aircraft cockpit according to claim 2 , wherein the head-up display device comprises two computers arranged to send display data along a main link to one of said two projectors respectively claim 2 , said two computers also being arranged to send display data along an auxiliary link to the other ...

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22-01-2015 дата публикации

SYSTEM AND METHOD FOR PROVIDING MODEL-BASED ALERTING OF SPATIAL DISORIENTATION TO A PILOT

Номер: US20150022380A1
Принадлежит:

A system and method monitor aircraft state parameters, for example, aircraft movement and flight parameters, applies those inputs to a spatial disorientation model, and makes a prediction of when pilot may become spatially disoriented. Once the system predicts a potentially disoriented pilot, the sensitivity for alerting the pilot to conditions exceeding a threshold can be increased and allow for an earlier alert to mitigate the possibility of an incorrect control input. 1. A method of alerting a crewmember of a vehicle of the possible existence of spatial disorientation , comprising:sensing a plurality of vehicle state parameters;passing the sensed vehicle state parameters through at least one transfer function associated with a human sensory system in order to estimate perceived vehicle state parameters;comparing the perceived vehicle state parameters with the sensed vehicle state parameters; andalerting the crewmember of the possibility of spatial disorientation if the discrepancy between perceived vehicle state parameters and sensed vehicle state parameters exceed a predetermined threshold.2. The method of further comprising:modifying the predetermined threshold in accordance with the comparison of the perceived vehicle state parameters with the sensed vehicle state parameters.3. The method of wherein the estimating of vehicle state parameters comprises:estimating using a computational model.4. The method of wherein the passing step comprises:passing the sensed vehicle state parameters through a transfer function associated with a human vestibular system.5. The method of wherein the vehicle is an aircraft and the sensing comprises:sensing a plurality of flight parameters.6. The method of wherein the predetermined threshold comprises:one of a degree of bank of the vehicle and a degree of pitch by the vehicle.7. The method of wherein the passing step comprises:passing the sensed vehicle state parameters through a transfer function associated with at least one of a ...

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17-04-2014 дата публикации

Method and device for communicating true runway braking performance using data from the flight data management systems of landed aircraft

Номер: US20140107872A1
Автор: Rado Zoltan Ivan
Принадлежит: Aviation Safety Technologies, LLC

A computer network for calculating a value for the true braking coefficient of friction for an aircraft runway or taxiway using data from one or more aircraft's flight data recorders or flight data management systems, and reporting the calculated value information to individuals and agencies including air traffic control, airport operations and maintenance, and aircraft pilots and ground crews is described and claimed herein. The data may be obtained in real-time by either an onboard or an off-aircraft high-power computing system, calculating the aircraft's true braking coefficient of friction, and reporting the calculated information to the individuals and agencies. 1. A computer network for calculating and distributing a true aircraft braking friction coefficient of an aircraft runway or aircraft taxiway , comprising:(A) A computer for obtaining aircraft property data directly or indirectly from an aircraft, wherein the aircraft property data comprises data pertaining to one or more of the following aircraft properties measured at various times for the aircraft and recorded on the aircraft's flight data management system: aircraft ground speed, aircraft brake pressure, aircraft longitudinal acceleration, aircraft engine thrust setting, aircraft reverse thrust setting, aircraft engine revolutions per minute, aircraft air speed, aircraft vertical acceleration, aircraft spoiler setting, aircraft airbrake setting, aircraft aileron setting, aircraft flap configuration, aircraft pitch, and aircraft autobrake setting;(B) Wherein the computer obtains at least some of the aircraft property data directly or indirectly from the aircraft's flight data management system; and(C) Wherein the computer calculates the true aircraft braking friction coefficient of the aircraft runway or aircraft taxiway using at least some of the aircraft property data.2. The computer network for calculating and distributing the true aircraft braking friction coefficient of the aircraft runway or ...

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10-02-2022 дата публикации

METHODS AND SYSTEMS FOR REPRESENTING FLIGHT MODE ANNUNCIATION INFORMATION ON A COCKPIT DISPLAY

Номер: US20220044576A1
Принадлежит: HONEYWELL INTERNATIONAL INC.

A method is provided for displaying information on a display device of an aircraft. The method comprises determining, by the processor, a first point along a flight path when a flight mode associated with a flight plan will be armed; determining, by the processor, a second point along the flight path when the flight mode associated with the flight plan will be engaged; determining, by the processor, a third point along the flight path when the flight mode associated with the flight plan will be disengaged; generating, by the processor, graphics data that represents the first point, the second point and the third point; incorporating, by the processor, the graphics data into a user interface that displays the flight path; and generating, by the processor, the user interface for display on the display device of the aircraft. 1. A method of displaying information on a display device of an aircraft , comprising:determining, by the processor, a first point along a flight path when a flight mode associated with a flight plan will be armed;determining, by the processor, a second point along the flight path when the flight mode associated with the flight plan will be engaged;determining, by the processor, a third point along the flight path when the flight mode associated with the flight plan will be disengaged;generating, by the processor, graphics data that represents the first point, the second point and the third point;incorporating, by the processor, the graphics data into a user interface that displays the flight path; andgenerating, by the processor, the user interface for display on the display device of the aircraft.2. The method of wherein the first point claim 1 , the second point claim 1 , and the third point indicate a vertical distance along the flight path.3. The method of wherein the first point claim 1 , the second point claim 1 , and the third point indicate a lateral distance along the flight path.4. The method of wherein the first point claim 1 , the ...

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24-01-2019 дата публикации

FUSION OF AVIATION-RELATED DATA FOR COMPREHENSIVE AIRCRAFT SYSTEM HEALTH MONITORING

Номер: US20190026963A1
Принадлежит:

Systems and methods to fuse aviation-related data systems for comprehensive aircraft system health monitoring are provided. One example method includes obtaining, by one or more computing devices, fault data indicative of a plurality of fault indications provided by a first plurality of components of an aircraft. The method includes obtaining, by the one or more computing devices, condition indicators describing the respective operational conditions of a second plurality of components of the aircraft. The method includes fusing, by the one or more computing devices, the fault data with the condition indicators to form a comprehensive data set. The method includes identifying, by the one or more computing devices, one or more causes of the plurality of fault conditions based at least in part on the comprehensive data set. One example system includes a data fuser, a cause identifier, and an alert generator. 1. A computer-implemented method for monitoring aircraft system health , the method comprising:obtaining, by one or more computing devices, fault data indicative of a plurality of fault indications provided by a first plurality of components of an aircraft;obtaining, by the one or more computing devices, condition indicators representative of respective operational conditions of a second plurality of components of the aircraft;fusing, by the one or more computing devices, the fault data with the condition indicators to form a comprehensive data set; andidentifying, by the one or more computing devices, one or more causes of the plurality of fault conditions based at least in part on the comprehensive data set.2. The method of claim 1 , further comprising:generating, by the one or more computing devices, one or more alerts that describe the one or more causes of the plurality of fault conditions; andproviding, by the one or more computing devices, the one or more alerts for display to maintenance personnel associated with the aircraft.3. The method of either of ...

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23-01-2020 дата публикации

Communication module for transmission of aircraft data

Номер: US20200028571A1
Автор: Jonathan Mark Miller
Принадлежит: Pratt and Whitney Canada Corp

Herein provided are methods and systems for method for transmitting data from an aircraft. A communication module for transmitting data from an aircraft comprises: a physical interface for removably coupling the communication module to an aircraft communication system which obtains the data; a data interface for obtaining at least one message for transmission from the aircraft communication system, the at least one message based on the data; and at least one radio for transmitting the at least one message via at least one antenna.

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29-01-2015 дата публикации

AVIONICS SYSTEM ADAPTED FOR EMPLOYING SMARTPHONE TO INPUT-OUTPUT FLIGHT DATA

Номер: US20150032296A1
Принадлежит:

A system and method configured to monitor aircraft flight performance data. The system includes a wireless transmitter in data communication with an avionics system of the aircraft, a portable wireless transceiver associated with the wireless transmitter, and a wireless database associated with the wireless transmitter. The method includes sensing flight performance data with the sensor, transmitting sensed flight performance data to the wireless transmitter, wirelessly transmitting the sensed flight performance data to the wireless database, and monitoring flight performance data with a display operably associated with the wireless database. 1. An aircraft , comprising:a sensor;an avionics system associated with the sensor;a wireless transmitter in data communication with the avionics system;wherein the avionics system is configured to monitor aircraft flight performance data from the sensor; andwherein the wireless transmitter is configured to wirelessly transmit aircraft flight performance data to the wireless database.2. The aircraft of claim 1 , further comprising:a wireless transceiver in data communication with the wireless transmitter;wherein the wireless transceiver is configured to receive and transmit aircraft flight performance data to the wireless database.3. The aircraft of claim 2 , wherein the wireless transceiver is portable.4. The aircraft of claim 3 , wherein the wireless transceiver is a smartphone.5. The aircraft of claim 2 , wherein the wireless transceiver is configured to transmit pilot identification to the wireless database.6. The aircraft of claim 2 , wherein the wireless transceiver is configured to upload data to the avionics system via the wireless transmitter.7. The aircraft of claim 6 , wherein the uploaded data is a flight planning data.8. The aircraft of claim 2 , wherein the wireless transmitter removably attaches to the wireless transceiver.9. The aircraft of claim 1 , wherein the wireless transmitter removably attaches to the ...

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29-01-2015 дата публикации

STRUCTURAL HEALTH MANAGEMENT WITH ACTIVE CONTROL USING INTEGRATED ELASTICITY MEASUREMENT

Номер: US20150032325A1
Принадлежит:

A system and method for actively controlling a structure is disclosed. At least one non-optimal event is identified in real-time based on at least one real-time elasticity measurement, if an event threshold exceeds a predetermined value. In response to an active control command, a control mechanism is then activated in real-time to compensate for the non-optimal event. 1. A control method for actively compensating for a non-optimal event in a structure , the method comprising:receiving a Vehicle Structural Health (VSH) threshold from a VSH threshold database in-real-time, wherein the VSH threshold is derived from real-time elasticity measurements comprising real-time relative measurements between measurement points and their respective design reference points on the structure to provide the real-time relative measurements related to design data;identifying at least one non-optimal event in real-time, if the VSH threshold exceeds a predetermined value; andcompensating for the at least one non-optimal event by activating at least one control mechanism in real-time in response to an active control command, wherein the at least one non-optimal event comprises structural twisting, bending or displacement induced by at least one force received on the structure.2. The method of claim 1 , wherein the structure comprises an aircraft claim 1 , a manned ground vehicle claim 1 , an unmanned ground vehicle claim 1 , an air vehicle claim 1 , a space vehicle claim 1 , a water vehicle claim 1 , an underwater vehicle claim 1 , a building claim 1 , or a windmill.3. The method of claim 1 , wherein the identifying of the at least one non-optimal event comprises identifying of at least one member selected from the group consisting of: a stress from wind shear on a lift surface claim 1 , a stress from a debris impact on a lift surface claim 1 , a stress from a gust on a lift surface claim 1 , a vibration claim 1 , a flutter claim 1 , a fuselage flexure claim 1 , an excessive bending of ...

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09-02-2017 дата публикации

Differential motion sensor

Номер: US20170038225A1
Принадлежит: Hamilton Sundstrand Corp

An electromechanical differential motion sensor is disposed to detect transverse motion of a first piece relative to a second piece. The sensor includes a base anchored to the first piece, a lever arm that engages the second piece, a hinge, a retention mechanism, and a fuse wire. The hinge connects the lever arm to the base, such that the lever arm rotates relative to the base when the second piece displaces laterally with respect to the first piece. The retention mechanism retains the electromechanical differential motion sensor in a closed position wherein a first jaw of the base is aligned with a second jaw of the lever arm. The fuse wire carries an electrical signal current, and extends through the jaws such that transverse motion of the second piece relative to the first piece deflects the sensor from the closed position to an open position, thereby severing the first fuse wire.

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12-02-2015 дата публикации

Exterior Aircraft Display System

Номер: US20150042494A1
Автор: Garrettson Brook W.
Принадлежит:

A method and apparatus for displaying information is presented. The information is sent from a number of sources to a display unit. The information is displayed through pixels located in the display unit. Heat is transferred in the display unit through a conductive path. 1. An apparatus comprising:pixels;a protective layer associated with the pixels, wherein the protective layer is substantially transparent in areas over the pixels; anda conductive path in the protective layer that transfers heat, wherein the pixels, the protective layer, and the conductive path form a display unit for an aircraft.2. The apparatus of claim 1 , wherein the conductive path conducts signals selected from at least one of power signals or data signals.3. The apparatus of further comprising:a number of circuits associated with the protective layer and connected to the conductive path.4. The apparatus of claim 3 , wherein the conductive path provides the signals to at least one of the pixels or the number of circuits.5. The apparatus of claim 1 , wherein the protective layer is selected from one of a flexible layer and a rigid layer.6. The apparatus of claim 3 , wherein at least one of the number of circuits and the pixels are encapsulated within the protective layer.7. The apparatus of claim 1 , wherein the protective layer has an opaque area in addition to the areas over the pixels that are substantially transparent.8. The apparatus of claim 7 , wherein the opaque area includes at least one of an image claim 7 , a color claim 7 , text claim 7 , or an applique.9. The apparatus of claim 1 , wherein the protective layer has a surface having a texture that causes a desired airflow over the protective layer.10. The apparatus of claim 1 , wherein the pixels perform at least one of receiving signals and transmitting the signals.11. The apparatus of claim 1 , wherein the display unit is located in a location selected from an exterior of the aircraft claim 1 , an interior of the aircraft claim 1 ...

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06-02-2020 дата публикации

SYSTEM AND METHOD FOR MONITORING THE STATE OF AN UNMANNED AIRCRAFT

Номер: US20200039638A1
Автор: Hunkel Peter
Принадлежит:

A system for monitoring the state of an unmanned aircraft includes a first communication unit, a second communication unit that can be integrated within the aircraft, a state transmission unit that can be integrated within the aircraft for transferring state data of the aircraft, a receiving unit integrated within the aircraft for receiving control commands, a computing unit assigned to the aircraft for validating the state of the aircraft, and an external control and monitoring unit connected to the computing unit. The computing unit executes a simulation model of the aircraft, which is based on numerical integration of a system of equations with a simulation state vector. The computing unit sends a warning signal to the control and monitoring unit on the occurrence of one or repeated instances of a model error correction term exceeding specified interval limits. 1. A system for monitoring the state of an unmanned aircraft , comprising:a first communication unit;a second communication unit that can be integrated into the aircraft;a state transmission unit that can be integrated into the aircraft to transmit state data of the aircraft;a computing unit assigned to the aircraft to validate the state of the aircraft; andan external control and monitoring unit connected to the computing unit;wherein the computing unit is configured to:carry out a simulation model of the aircraft in question, wherein the simulation model is based on numerical integration of a system of equations with a simulation state vector;repeatedly track the simulation state vector of at least one subset of previously measured flight status data by stepwise adjustment of at least one functional element of the simulation model by at least one model error correction term; andmonitor the variation of the at least one model error correction term and send a warning signal to the control and monitoring unit if the model error correction term exceeds predetermined interval limits once or multiple times; ...

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07-02-2019 дата публикации

STRUCTURAL PI JOINT WITH INTEGRATED FIBER OPTIC SENSING

Номер: US20190041241A1
Принадлежит:

A structural health monitoring system includes a first component and a second component associated at a joint. At least one sensor is embedded within the joint to monitor a health of at least one of the first component, the second component, and the joint. 1. A structural health monitoring system comprising:a first component;a second component, wherein the second component and the first component are associated at a joint;at least one sensor embedded within the joint to monitor a health of at least one of the first component, the second component, and the joint.2. The structural health monitoring system of claim 1 , wherein the sensor includes at least one fiber optic cable.3. The structural health monitoring system of claim 2 , wherein the sensor includes a plurality of fiber optic cables.4. The structural health monitoring system of claim 3 , wherein at least a portion of the plurality of fiber optic cables intersect one another.5. The structural health monitoring system of claim 1 , wherein the joint is defined by a preform.6. The structural health monitoring system of claim 5 , wherein the preform further comprises:a first portion for receiving the first component; anda second portion for mounting to the second component, the first portion and the second portion being integrally formed.7. The structural health monitoring system of claim 6 , wherein the first portion extends at an angle to the second portion.8. The structural health monitoring system of claim 5 , wherein the preform includes an opening for receiving at least one of the first component and the second component claim 5 , the at least one sensor being disposed within the opening.9. The structural health monitoring system of claim 1 , wherein the structural health monitoring system is applied to an aircraft.10. The structural health monitoring system of claim 9 , wherein at least one of the first component and the second component is a skin of the aircraft.11. The structural health monitoring system ...

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12-02-2015 дата публикации

DISPLAY SYSTEMS AND METHODS FOR PROVIDING DISPLAYS INDICATING A REQUIRED TIME OF ARRIVAL

Номер: US20150045989A1
Принадлежит:

A method for providing a display to a flight crew of an aircraft includes receiving a required time of arrival (RTA) control instruction for arriving at a particular waypoint at a particular time, calculating an initial required aircraft speed at which the aircraft is required to fly in order to arrive at the particular waypoint at the particular time, and providing a flight display comprising a speed tape. The method further includes receiving an input accepting the RTA control instruction and calculating an updated required aircraft speed at which the aircraft is required to fly in order to arrive at the particular waypoint at the particular time. Still further, the method includes updating the flight display comprising displaying the updated RTA target speed on the speed tape using a second symbology that is different from the first symbology and discontinuing the display of the first symbology. 1. A method for providing a display to a flight crew of an aircraft comprising the steps of:receiving a required time of arrival (RTA) control instruction for arriving at a particular waypoint at a particular time;calculating an initial required aircraft speed at which the aircraft is required to fly in order to arrive at the particular waypoint at the particular time;providing a flight display comprising a speed tape, wherein the speed tape comprises an initial RTA target speed that is graphically displayed using a first symbology, wherein the initial RTA target speed correlates with the initial required aircraft speed, and wherein providing the flight display is not accompanied with a concurrent aircraft speed change to match the initial target speed;receiving an input accepting the RTA control instruction;calculating an updated required aircraft speed at which the aircraft is required to fly in order to arrive at the particular waypoint at the particular time, wherein, if a change in flight conditions has occurred between the steps of calculating the initial required ...

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18-02-2016 дата публикации

SYSTEM FOR EXTERNAL ANNUNCIATION OF TIRE PRESSURE

Номер: US20160046158A1
Принадлежит:

A system for measuring tire pressure on an aircraft includes a wheel with a tire pressure. A tire pressure sensor on the wheel may be configured to output an electronic measurement of the tire pressure. A transmission device may be electrically coupled to the first tire pressure sensor and configured to transmit the first electronic measurement. A hubcap may be on the first wheel with a transmission device mounted to the hubcap. 1. A system for measuring tire pressure on an aircraft , comprising:a first wheel including a first tire pressure;a first tire pressure sensor on the first wheel configured to output a first electronic measurement of the first tire pressure;a first transmission device electrically coupled to the first tire pressure sensor and configured to transmit the first electronic measurement.2. The system of claim 1 , further comprising a hubcap at a proximal region of the first wheel claim 1 , wherein the first transmission device is mounted to the hubcap.3. The system of claim 2 , wherein the first transmission device is an infrared light-emitting diode.4. The system of claim 2 , further including an axle telemetry unit claim 2 , wherein the axle telemetry unit is in electromagnetic communication with the hubcap.5. The system of claim 1 , further comprising:a second wheel including a second tire pressure;a second tire pressure sensor on the second wheel configured to output a second electronic measurement of the second tire pressure; anda first hubcap at a proximal region of the first wheel, wherein the first hubcap is configured to receive the second electronic measurement of the second tire pressure.6. The system of claim 5 , wherein:the first wheel is mounted on a nose gear assembly; andthe second wheel is mounted on a main gear assembly.7. The system of claim 6 , further comprising:a second hubcap at a proximal region of the second wheel, wherein the second hubcap is configured to receive the first electronic measurement of the first tire ...

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24-02-2022 дата публикации

TAKE-OFF PERFORMANCE PREDICTION AND ALERTING SYSTEM

Номер: US20220058963A1
Принадлежит: GULFSTREAM AEROSPACE CORPORATION

The aircraft take-off awareness system predicts and informs the pilot about where on the runway certain safety speeds will be achieved. A processor coupled to receive inertial data from the aircraft computes an aircraft weight estimate based at least in part upon the inertial data. The processor then computes a future acceleration prediction based on the computed aircraft weight estimate. Using the future acceleration prediction, the processor then computes the position of various warning reference distances corresponding to predicted positions on the runway at which said certain safety speeds will be achieved. The processor generates a display that it dynamically updates as the reference distances change as the aircraft proceeds down the runway during take-off or aborted take-off. 1. An aircraft take-off awareness system to predict and inform the pilot about where on the runway certain safety speeds will be achieved , comprising:a processor coupled to receive inertial data from the aircraft and programmed to compute an aircraft weight estimate based at least in part upon the inertial data;the processor being further programmed to compute a future acceleration prediction based on the computed aircraft weight estimate;the processor being further programmed to compute and inform the pilot about at least one warning reference distance using the computed future acceleration prediction, the warning reference distance corresponding to predicted positions on the runway at which said certain safety speeds will be achieved.2. The system of wherein the processor is programmed to compute the aircraft weight estimate further based on a computed thrust estimation claim 1 , and a computed drag estimation.3. The system of wherein the processor is programmed to compute the aircraft weight estimate by using the inertial data to compute a current acceleration estimate.4. The system of wherein the processor is programmed to compute the future acceleration prediction further based on ...

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15-02-2018 дата публикации

Auxiliary Security System for Aircraft Black Box System

Номер: US20180044034A1
Принадлежит:

A multifunction avionics server provide for the execution of both certified and uncertified applications in data-serving capacities in which one certified application provides near real-time transmission of flight data recorder type of data. By combining these functions, improved aircraft monitoring is obtained without significant cost or weight penalties. 1. An avionics server for supplementing black box operation by real-time transmission of black box data comprising:at least one electronic computer executing a stored program;an avionics navigation bus interface communicating with the electronic computer;a flight data recorder bus interface communicating with the electronic computer and adapted to communicate with a flight data recorder; anda long-range wireless transmitter;wherein the stored program executes to:(a) serve flight-related information over the avionics navigation bus to cockpit display devices; and(b) receive data from the flight recorder bus interface and transmit that data to a receiver remote from an aircraft holding the avionics server using the long-range wireless transmitter.2. The avionics server of wherein flight-related information is in fixed presentations of precomposed data selected from the group consisting of: electronic pilot manuals claim 1 , flight checklists claim 1 , reference documents claim 1 , equipment lists claim 1 , and maintenance manuals.3. The avionics server of wherein the fixed presentations of precomposed data are generated by programs executed by the at least one electronic computer and classified as Type-A programs.4. The avionics server of wherein flight-related information is dynamic display information selected from the group consisting of: moving map displays claim 1 , dynamic weather charts claim 1 , and merging and spacing displays.5. The avionics server of wherein the dynamic display information is generated by programs executed by the at least one electronic computer and classified as Type-B programs.6. The ...

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18-02-2016 дата публикации

System and method for location of aircraft

Номер: US20160047880A1
Автор: Albert D. Helfrick

A system and method are provided that includes an aircraft secondary radar transponder activity detector that monitors an aircraft's transponder transmissions and activates an emergency locator transmitter to begin transmitting should the aircraft transponder transmissions cease to help locate an aircraft that may have become undetectable by conventional aircraft surveillance and tracking systems.

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06-02-2020 дата публикации

EXIT DOOR INDICATION SYSTEM

Номер: US20200043307A1
Автор: Lapujade Philippe
Принадлежит: Goodrich Lighting Systems, Inc.

An aircraft emergency exit door indication system may comprise a first plurality of light sources, a controller, and a first sensor associated with a first exit door. The first sensor feedback signal indicates an availability for egress through the first exit door. The first plurality of light sources is operated by the controller based upon the first sensor feedback signal. The light sources may be lights that already exist in an aircraft such as ceiling wash lights, sidewall wash lights, floor path lights, dome lights, or passenger service unit lights. The system may include a second plurality of light sources logically separated from the first plurality of light sources based upon its location relative to the first exit door and a second exit door. 1. An aircraft emergency exit door indication system , comprising:a first plurality of light sources;a controller in electronic communication with the first plurality of light sources;a first sensor associated with a first exit door;wherein the controller receives a first sensor feedback signal from the first sensor indicating an availability for egress through the first exit door;the first plurality of light sources is operated by the controller based upon the first sensor feedback signal to indicate a direction of egress with respect to the first exit door, wherein the first plurality of light sources is energized to vary an illumination of the first plurality of light sources in response to being operated by the controller.2. The aircraft emergency exit door indication system of claim 1 , wherein the first plurality of light sources include at least one of a ceiling wash light claim 1 , a sidewall wash light claim 1 , a floor path light claim 1 , a dome light claim 1 , or a passenger service unit light.3. The aircraft emergency exit door indication system of claim 1 , further comprising:a second plurality of light sources, the controller in electronic communication with the second plurality of light sources; anda ...

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15-02-2018 дата публикации

FREQUENCY-ADAPTABLE STRUCTURAL HEALTH AND USAGE MONITORING SYSTEM (HUMS) AND METHOD WITH SMART SENSORS

Номер: US20180047225A1
Принадлежит:

A structural health monitoring system comprising intelligent sensors and serial communications devices interconnecting the sensors, data acquisition units and a programmable logic controller (PLC). The intelligent sensors are individually programmable and can be tuned to listen to specific frequencies based on a scaling factor based on the sensor's location in the system being monitored, a set of pre-known frequencies based on the sensor's location in the system being monitored, and the output of a central frequency-based system sensor. An aircraft flight control application of a method embodying the present invention includes anomaly detection based on comparing one or more preprogrammed flight plan regimen variables with actual aircraft performance parameters, and taking appropriate corrective action. 1. A health and usage monitoring system (HUMS) for an aircraft with an operating parameter , which HUMS includes:an intelligent sensor mounted on the aircraft and configured for sensing said operating parameter;a communication interface connected to said intelligent sensor and receiving operating parameter output therefrom;a data acquisition unit connected to said communication interface and receiving said operating parameter data output therefrom;a programmable logic controller (PLC) connected to said data acquisition unit and receiving data output therefrom, said PLC preprogrammed with flight regimen operating parameters for said aircraft; andsaid PLC including an anomaly detection function configured for comparing said preprogrammed flight regimen with an actual flight parameter and providing an anomaly output in response to detecting an operating parameter anomaly.2. The HUMS according to claim 1 , which includes:an output device connected to said PLC and configured for receiving output therefrom, said output device identifying said anomaly condition to a user or a ground control system for said aircraft.3. The HUMS according to claim 1 , which includes:said ...

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03-03-2022 дата публикации

SYSTEM AND METHOD FOR ENHANCED VEHICLE DATA CONNECTIVITY

Номер: US20220063833A1
Принадлежит: GE AVIATION SYSTEMS LLC

A method of operating an aircraft interface device may comprise receiving a request for a data dictionary from an electronic flight bag application and transmitting the data dictionary to the electronic flight bag application. The data dictionary may comprise a mapping between a plurality of parameters associated with an aircraft and a plurality of parameter identifiers. Values of the parameters may be retrieved by the aircraft interface device. The method may also include receiving a request for values of one or more of the parameters from the electronic flight bag, retrieving values of the parameters, and transmitting the values of the parameters to the electronic flight bag application. 1. A method of operating an aircraft interface device comprising:receiving, from an electronic flight bag application, a request for a data dictionary, wherein the data dictionary comprises a mapping between a plurality of parameters associated with an aircraft and a plurality of parameter identifiers, and wherein values of the parameters may be retrieved by the aircraft interface device; andtransmitting the data dictionary to the electronic flight bag application.2. The method of claim 1 , wherein the plurality of parameter identifiers comprise a parameter number associated with each of the plurality of parameters associated with the aircraft.3. The method of claim 1 , wherein the plurality of parameter identifiers comprise a parameter name associated with each of the plurality of parameters associated with the aircraft.4. The method of claim 1 , wherein the plurality of parameters associated with the aircraft depend on a model of the aircraft.5. The method of claim 1 , further comprising:receiving, from the electronic flight bag application, a request for the values of one or more of the plurality of parameters associated with the aircraft;retrieving values of the one or more of the plurality of parameters; andtransmitting the values of the one or more of the plurality of ...

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03-03-2022 дата публикации

CREW ALERTING SYSTEMS AND METHODS FOR MOBILE PLATFORMS

Номер: US20220063835A1
Автор: OUELLETTE Benoit
Принадлежит:

Systems, devices and methods for alerting a crew of an aircraft or other mobile platform of a relevant condition associated with the aircraft are disclosed. One exemplary method comprises receiving data indicative of an existence of the relevant condition associated with the aircraft; receiving data indicative of a substantially real-time value of a dynamic parameter associated with the relevant condition; and displaying an awareness-enhancing indication associated with the relevant condition in a display area of the crew alerting system of the aircraft. The awareness-enhancing indication comprises a textual message and a supplemental indication indicative of the substantially real-time value of the dynamic parameter associated with the relevant condition. In various embodiments, the supplemental indication may be textual or graphical. The supplemental indication may also be indicative of a target value of the dynamic parameter.

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19-02-2015 дата публикации

Method for Monitoring Autonomous Accelerated Aircraft Pushback

Номер: US20150051757A1
Принадлежит:

A method for monitoring an autonomous accelerated pushback process in an aircraft equipped with an engines-off taxi system is provided to maximize safety and facilitate the accelerated pushback process. The aircraft is equipped with a monitoring system including a number of different kinds of sensors and monitoring devices positioned to maximally monitor the aircraft's exterior ground environment and communicate the presence or absence of obstructions in the aircraft's path while the pilot is controlling the engines-off taxi system to drive the aircraft in reverse away from a terminal gate and then turn in place at a selected location before driving forward to a taxiway. The sensors and monitoring devices may be a combination of cameras, ultrasound, global positioning, radar, and LiDAR or LADAR devices, and proximity sensors located at varying heights adapted to continuously or intermittently scan or sweep the aircraft exterior and ground environment during aircraft ground movement. 1. A method for monitoring an autonomous accelerated pushback process in an aircraft equipped with an engines-off taxi system , comprising:(a) equipping an aircraft with an engines-off taxi system controllable by a pilot of said aircraft to turn and move an aircraft in reverse and forward directions without reliance on operation of the aircraft main engines or an external tow vehicle;(b) further equipping said aircraft with a monitoring system comprising a plurality of different kinds of sensors or sensor devices adapted to be positioned on an exterior of said aircraft at multiple locations and heights above a ground surface selected to monitor a maximum portion of said aircraft's ground environment and space surrounding said aircraft's exterior;(c) activating said monitoring system so that said plurality of sensors or sensor devices is operable to monitor said aircraft exterior environment and to communicate information relating to a presence or absence of obstructions in a defined ...

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25-02-2016 дата публикации

HEALTH MANAGEMENT UNIT AND METHOD FOR MONITORING HEALTH INFORMATION AND METHOD OF REPORTING CRITICAL FAILURE INFORMATION

Номер: US20160052640A1
Принадлежит:

A health management unit for an aircraft and method of reporting critical failure information, in an aircraft having a health management unit that includes determining by the health management unit a potential catastrophic event during the flight of the aircraft based on data received by the health management unit and assembling by the health management unit data indicative of a report of the aircraft state of operation upon the determining of a potential catastrophic event. 1. (canceled)2. The method of wherein the determining the potential catastrophic event comprises receiving data from at least one system in the aircraft.3. (canceled)4. The method of wherein the transmitting the predefined summary report comprises repeatedly transmitting the predefined summary report.5. The method of wherein the assembling of data further comprises aggregating claim 16 , updated data and assembling the aggregated updated data.6. The method of wherein the transmitting the assembling of data further comprises transmitting the aggregated updated data.7. The method of wherein transmitting the predefined summary report off of the aircraft comprises selecting off-board interfaces to transmit the predefined summary report.8. The method of wherein the assembling of data comprises establishing connections to off-board interfaces.9. (canceled)10. The method of wherein the assembling of data comprises collecting data related to a critical state of the aircraft claim 16 , operational data claim 16 , or location data.11. The method of wherein the assembling of data comprises collecting data that aids in locating the aircraft or determining potential issues with the aircraft.12. (canceled)13. (canceled)14. (canceled)15. (canceled)16. A method of reporting critical failure information claim 16 , in an aircraft having a health management unit claim 16 , the method comprising:aggregating data, by the health management unit, from multiple systems of the aircraft;determining, by the health ...

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25-02-2016 дата публикации

AIRCRAFT OPERATING AND POSITION INFORMATION DISPLAY SYSTEM AND METHOD

Номер: US20160052641A1
Принадлежит: HONEYWELL INTERNATIONAL INC.

A method of displaying aircraft operating and position information with an electronic display unit comprises determining a position of a first aircraft at an airport; determining an optimum speed range of the first aircraft; determining a first aircraft speed of the first aircraft; displaying on a screen of the display unit a map of at least part of the airport; displaying a first aircraft symbol on the map, the first aircraft symbol displayed in a position on the map indicative of position of the first aircraft; and displaying an optimum speed range symbol having a lower bound end and a higher bound end in a position on the map such that the first aircraft symbol is between the lower bound end and the higher bound end when the first aircraft speed is within the optimum speed range. 1. A method of displaying aircraft operating and position information with an electronic display unit , comprising:determining a position of a first aircraft at an airport;determining an optimum speed range of the first aircraft, with a performance model;determining a first aircraft speed of the first aircraft with a speed sensor;displaying on a screen of the display unit a map of at least part of the airport, including runways and taxiways, from map data in an airport database;displaying a first aircraft symbol on the map, the first aircraft symbol displayed in a position on the map indicative of position of the first aircraft; anddisplaying an optimum speed range symbol, the optimum speed range symbol having a lower bound end and a higher bound end, on the map; andwherein the optimum speed range symbol is displayed in a position on the map such that the first aircraft symbol is between the lower bound end and the higher bound end when the first aircraft speed is within the optimum speed range.2. The method of claim 1 , wherein the optimum speed range symbol is placed in a position on the map such that the first aircraft symbol is on a lower bound side of the optimum speed range symbol ...

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13-02-2020 дата публикации

SYSTEM AND METHOD OF PROTECTION OF AIRCRAFT FROM FOREIGN OBJECT STRIKES

Номер: US20200047915A1
Принадлежит:

An aircraft structure protected from collisions with foreign objects includes a first support proximate to an aircraft structure root; first sheets attached to the first support to form a first leading edge portion of the aircraft structure; a second support proximate to an outer end of the aircraft structure; second sheets attached to the second support to form a second leading edge portion; and a door including one or more ribs disposed between the first and second supports and configured to give shape to a third leading edge portion of the aircraft structure; and third sheets, attached to the ribs to form the third portion of the leading edge; wherein the first support, the first sheets, the second support, the second sheets, the one or more ribs, and the third sheets are disposed to mitigate damage from a foreign object collision by absorbing kinetic energy from a collision. 1. An aircraft structure protected from collisions with foreign objects comprising:a first support proximate to a root of the aircraft structure;one or more first sheets comprising a first material and attached to the first support to form a first portion of a leading edge of the aircraft structure;a second support proximate to an outer end of the aircraft structure;one or more second sheets comprising a second material and attached to the second support to form a second portion of the leading edge; and one or more ribs disposed between the first support and the second support and configured to give shape to a third portion of a leading edge of the aircraft structure; and', 'one or more third sheets comprising a third material, attached to the ribs to form the third portion of the leading edge;, 'a door comprisingwherein the first support, the one or more first sheets, the second support, the one or more second sheets, the one or more ribs, and the one or more third sheets are disposed to mitigate damage from a collision with a foreign object by absorbing kinetic energy from a collision.2. ...

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26-02-2015 дата публикации

Aircraft Monitoring System

Номер: US20150054663A1
Принадлежит:

A method and apparatus for monitoring an aircraft. A pilot control input signal is received. A response of a control surface system controlled by a flight control model is identified using the pilot control input signal. An alert is generated when the control surface system reaches a threshold with respect to the control surface system becoming saturated. 1202. A method for monitoring an aircraft () , the method comprising:{'b': '224', 'receiving a pilot control input signal ();'}{'b': 206', '230', '224, 'identifying a response of a control surface system () controlled by a flight control model () using the pilot control input signal ();'}{'b': 240', '206', '241', '206, 'generating an alert () when the control surface system () reaches a threshold () with respect to the control surface system () becoming saturated; and'}{'b': 408', '436', '464', '236', '224, 'displaying, via a first indicator (, , or ) on a graphical user interface (), the pilot control input signal ();'}{'b': 412', '236', '206', '224, 'displaying, via a second indicator () on the graphical user interface (), a command sent to the control surface system () in response to the pilot control input signal (); and'}{'b': 413', '469', '490', '236, 'displaying, via a third indicator (, , or ) on the graphical user interface (), a response of the aircraft.'}2. The method of further comprising:{'b': 442', '468', '444', '236', '206, 'displaying, via a fourth indicator (, , or ) on the graphical user interface (), the response of the control surface system () to the command.'}3. The method of further comprising:{'b': 206', '236, 'modifying a display of the response of the control surface system () based on a range for a position of a control surface prior to displaying the response on the graphical user interface ();'}{'b': 224', '408', '436', '464', '422', '454', '478', '422', '454', '478', '224, 'wherein the pilot control input signal () is displayed via a first graphical element (, , or ) and a second ...

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23-02-2017 дата публикации

Indication device as well as door arrangement and aircraft with such an indication device

Номер: US20170050744A1
Принадлежит:

An indicating device for indicating a non-authorized opening of an aircraft door comprising a sensor for detecting a distance from the sensor to an object, a signaling device, a reset device coupled to the signaling device allowing the signaling device to be set into a first state following a reset operation, an enabling device, providing as an output signal, selectively, a disable signal and an enable signal, and a control device connected to the sensor, the signaling device and the enabling device. On receiving the disable signal, the control device changes into a first operating mode and on receiving the enable signal it changes into a second operating mode in which, based upon the signal received from sensor, it detects a distance change between the sensor and the object, and, on detecting a change, sets the signaling device into a second state until the reset operation is completed. 1. An indicating device for indicating an unauthorized opening of a door of an aircraft parked on the ground , comprising:a sensor configured to detect a distance between the sensor and an object that is located inside a detection zone in front of the sensor,a signaling device, which has a first state and a second state,a reset device that is connected to the signaling device and that is configured to set said signaling device into the first state when a user carries out a predetermined reset operation,an enabling device, which is configured to provide as an output signal, selectively, a predetermined disable signal and a predetermined first enable signal, anda control device, which is connected to the sensor, the signaling device and the enabling device and is configured:to change into a first operating mode when receiving the disable signal andto change into a second operating mode when receiving the first enable signal, in which second operating mode it detects, based upon a sensor signal provided by the sensor and characteristic for the distance between the sensor and the object ...

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25-02-2021 дата публикации

CHARACTERIZATION OF A CLOUD ATMOSPHERE USING LIGHT BACKSCATTERED AT TWO ANGLES

Номер: US20210055422A1
Принадлежит:

Apparatus and associated methods relate to determining an effective size, quantity, shape, and type of water particles in a cloud atmosphere based on differences in amplitudes of optical signals backscattered at different backscattering angles. Off-axis backscattering—backscattering at angles other than 180 degrees—is affected by the effective size, quantity, shape, and type of water droplets. Detected amplitudes of optical signals that are backscattered at different angles are used to indicate the effective size, quantity, shape, and type of water particles in the cloud atmosphere. In some embodiments, optical emitters and detectors are configured to measure amplitudes of optical signals backscattered at backscattering angles of both on-axis—180 degrees—and off-axis varieties. 1. A system for characterizing a cloud atmosphere , the system comprising:an optical emitter configured to emit an optical beam into the cloud atmosphere;a first optical detector configured to detect a first portion of the optical beam backscattered by the cloud atmosphere at a first backscatter angle;a second optical detector configured to detect a second portion of the optical beam backscattered by the cloud atmosphere at a second backscatter angle different from the first backscatter angle; anda cloud-characteristic calculator configured to calculate one or more cloud parameters of the cloud atmosphere based on the detected first and second portions.2. The system of claim 1 , wherein cloud-characteristic calculator is configured to calculate one or more cloud parameters of the cloud atmosphere based on a ratio of the detected first and second portions.3. The system of claim 1 , wherein cloud-characteristic calculator is configured to calculate one or more cloud parameters of the cloud atmosphere based on a difference between the detected first and second portions.4. The system of claim 1 , wherein a magnitude of a difference between the first and second backscatter angles is at least 3 ...

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